ISS Russian Segment User Manual
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S.P.Korolev Rocket and Space Corporation Energia ISS Russian Segment Инв.№ подл Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата User Manual ОАО «РКК «Энергия» им. С.П. Королева», 2004 2011 Подпись и дата Инв. № дубл. Взам. инв. № Подпись и дата Инв.№ подл. Table of Contents 1 Introduction………………………………………………………………………....3 2 Ground rules………………………………………………………………………...4 3 General data on the ISS RS resources at different stages of its deployment……5 3.1 ISS RS consisting of SM and DC1……………………………………………….5 3.2 ISS RS consisting of SM, DC1 and MRM2……………………………………...8 3.3 ISS RS consisting of SM, DC1, MRM2 and MRM1…………………………..11 3.4 ISS RS consisting of SM, MRM2, MRM1 and MLM…………………………14 3.5 Characteristics of communication links and downlinking……………………17 3.6 Trajectory and navigation support for space experiments…………………...19 3.7 The list of photographic and video equipment onboard ISS RS……………..22 3.8 Equipment for still photography Specifications……………………………….23 3.9 Video equipment………………………………………………………………....30 4 Capabilities supporting scientific equipment operation on ISS RS modules….37 4.1 Service module (СМ)……………………………………………………………37 4.2 Docking compartment No.1 (DC1)……………………………………………..54 4.3 Mini Research Module 2 (MRM2)……………………………………………...58 4.4 Mini Research Module 1 (MRM1)……………………………………………...66 4.5 Multipurpose laboratory module (MLM)……………………………………...70 5 Cargo certification………………………………………………………………...89 5.1 Documents used in the course of certification…………………………………90 5.2 Scientific equipment tests……………………………………………………….92 6 Specifications for experimental equipment delivered to ISS………………….102 6.1 Specifications for equipment transported in Russian spacecraft Progress and Soyuz………………………………………………………………………………...102 6.2 Specifications for the equipment stored and operated onboard ISS RS……120 6.3 Safety requirements……………………………………………………………150 6.4 A typical crew day plan during implementation of the standard mode……159 6.5 Acoustic environment in the ISS RS modules………………………………..160 6.6 Cargo integration………………………………………………………………166 Attachment A……………………………………………………………………….186 П40463 Изм. Лист № докум. Подп. Дата Лист 2 1 Introduction This Manual provides basic information that designers of experiments and payloads that are proposed to be conducted and installed in the Russian Segment of the International Space Station (ISS RS) need to know in order to correctly state specifications when drawing up statements of work for space experiments and scientific equipment, as well as to conduct a preliminary feasibility analysis of the experiments proposed for ISS RS. It provides general information about ISS RS resources at different stages of its deployment, as well as about resources of its individual elements. Special attention is given to the issues related to payload delivery and in-orbit operation and returning experimental results to earth. All the payloads installed on ISS RS (Scientific Equipment (SE)) are included into the Mission Payload Facility (MPF). The Manual describes the ISS RS MPF architecture and provides a brief description of its components. It provides a description of workstations for accommodating scientific equipment, SE, the principles of SE control, and methods of downlinking data from the SE. It describes the SE operational environments within the ISS RS modules and within the transportation vehicles Soyuz and Progress. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата mission payloads that support the conduct of space experiments, resources provided for П40463 Изм. Лист № докум. Подп. Дата Лист 3 2 Ground rules To meet the necessary requirements for SE development, testing, delivery, accommodation and functioning, a Mission Payload Facility is established onboard ISS RS. Included in the MPF are: - scientific equipment; - mechanical adapters; - science support equipment; - cables. In order to achieve the most efficient use of resources provided by the space station for conducting research throughout its life (during which time some research objectives may become irrelevant, the research methodology may change, and scientific equipment may fail or become obsolete), the MPF is based on the principles of unification and integratedness. The unification principle calls for the use of replaceable payload technology which implies that virtually any kind of scientific equipment can be delivered and put into support installation and adaptation of delivered SE (built to meet the relevant requirements) from the standpoint of mechanical, electrical, data and other interfaces. SE control, data support, temperature control and vacuumization onboard ISS RS are provided by the onboard support systems that are not included into MPF. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата operation immediately in orbit. In order to implement such technology, the MPF will П40463 Изм. Лист № докум. Подп. Дата Лист 4 4 3 General data on the ISS RS resources at different stages of its deployment 3.1 ISS RS consisting of SM and DC1 Resources allocated to the MPF include: - the working volume allocated (at SM and DC1): up to 1 m3; - power supply: up to 0.3 kW (daily average) and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation; - heat removal capacity: up to 0.3 kW (daily average) (the balance is achieved taking into account the heat loss through the SM hull); - the number of workstations on the outer surface: 4 pcs. on the SM (8 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account) - payload data downlink capacity (maximum, via TM IU unit): up to 2 MB per a session; - ISS attitude control mode (nominal): Orbital Coordinate System (OCS); - ISS OCS attitude control accuracy: ± 10 angular minutes; Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата - ISS angular rate stabilization accuracy: 0.005 deg/s; - the number of telemetered parameters: up to 212; - the list of electrical interfaces available for MPF: -RS-232; -RS-422; -RS-485; -Ethernet; -USB; - HF with wave impedance coefficients: 75 Ohm and 50 Ohm; - discrete control commands; - the number of vaccumization interfaces for MPF: 1 pc. The MPF cargo traffic to ISS RS is planned based on the following assumptions: - delivery of cargo to ISS RS onboard Progress M (M1) logistics spacecraft on average up to 600 kg per year; - return from ISS RS of up to 110 kg of payloads per year. П40463 Изм. Лист № докум. Подп. Дата Лист 5 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The external appearance of ISS RS in the above configuration is shown in Fig.3.1 П40463 Изм. Лист № докум. Подп. Дата Лист 6 Инв.№ подл. Изм. Лист № докум. Подп. Дата П40463 Лист 7 Подпись и дата SM Подпись и дата FGB Fig. 3.1 – ISS RS configuration consisting of SM and DC1 Progress-M DC1 Инв. № дубл. Progress-M Взам. инв. № Soyuz TMA 3.2 ISS RS consisting of SM, DC1 and MRM2 Resources allocated to the MPF include: - allocated working volume of up to 1 m3 on the SM and up to 0.2 m3 on MRM2; - power supply: - on SM and DC1 up to 0.3 kW (daily average) and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation; - on MRM2 up to 0.1 kW (daily average); - heat rejection capacity: up to 0.3 kW (daily average) (the balance is achieved taking into account the heat loss through the SM hull); - the number of workstations on the outer surface: -4 pcs. on the SM (8 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account) -5 pcs. on MRM2 (7 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account); Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата - payload data downlink capacity (maximum, via TM IU unit): up to 2 MB per a session; - ISS attitude control mode (nominal): Orbital Coordinate System (OCS); - ISS OCS attitude control accuracy : ± 10 angular minutes; - ISS angular rate stabilization accuracy: 0.005 deg/s; - the number of telemetered parameters: up to 212 (SM) and up to 50 (MRM2); - the list of electrical interfaces available for MPF: -RS-232; -RS-422 (only on SM); -RS-485 (only on SM); -Ethernet; -USB; - HF with wave impedance of 75 Ohm and 50 Ohm (only on SM); - discrete control commands; - the number of vaccumization interfaces for MPF: 1 pc. (on MRM2). П40463 Изм. Лист № докум. Подп. Дата Лист 8 The MPF cargo traffic to ISS RS is planned based on the following assumptions: - delivery of cargo to ISS RS onboard Progress M (M1) logistics spacecraft: on average up to 600 kg per year; - return from ISS RS of up to 110 kg of payloads per year. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The external appearance of ISS RS in the above configuration is shown in Fig.3.2 П40463 Изм. Лист № докум. Подп. Дата Лист 9 Инв.№ подл. Изм. Лист № докум. Подп. Дата П40463 Лист 10 Подпись и дата Взам. инв. № Progress M DC1 SM Progress M Fig. 3.2 – ISS RS configuration consisting of SM, DC1 and MRM2 MRM2 Soyuz TMA Подпись и дата Soyuz TMA FGB Инв. № дубл. 3.3 ISS RS consisting of SM, DC1, MRM2 and MRM1 Resources allocated to the MPF include: - allocated working volume of : up to 1 m3 on SM, up to 0.2 m3 on MRM2 and up to 3 m3 on MRM1; - power supply: - on SM and DC1 up to 0.3 kW (daily average) and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation; - on MRM2 up to 0.1 kW (daily average); - on MRM1 up to 0.1 kW (daily average); - heat rejection capacity: - on SM, DC1 and MRM2 up to 0.3 kW (daily average) (the balance is achieved taking into account the heat loss through the SM hull); - on MRM1 up to 0.1 kW (daily average); - the number of workstations on the outer surface: Взам. инв. № Инв. № дубл. Подпись и дата -4 pcs. on the SM (8 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account); -5 pcs. on MRM2 (7 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account); - payload data downlink capacity (maximum, via TM IU unit): up to 2 MB per a session; - ISS attitude control mode (nominal): Orbital Coordinate System (OCS); - ISS OCS attitude control accuracy : ± 10 angular minutes; - ISS angular rate stabilization accuracy: 0.005 deg/s; - the number of telemetered parameters: up to 212 (SM), up to 50 (MRM2) and up to 36 Инв.№ подл. Подпись и дата (MRM1); - the list of electrical interfaces available for MPF: -RS-232; -RS-422 (only on SM); -RS-485 (only on SM); П40463 Изм. Лист № докум. Подп. Дата Лист 11 -Ethernet; -USB; - HF with wave impedance of 75 Ohm and 50 Ohm (only on SM); - discrete control commands (on SM and MRM2); - the number of vaccumization interfaces for MPF: 1 pc on MRM2 and 1 pc on MRM1. The MPF cargo traffic to ISS RS is planned based on the following assumptions: - delivery of cargo to ISS RS onboard Progress M (M1) logistics spacecraft: on average up to 600 kg per year; - return from ISS RS of up to 110 kg of payloads per year. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The external appearance of ISS RS in the above configuration is shown in the figure П40463 Изм. Лист № докум. Подп. Дата Лист 12 Инв.№ подл. Изм. Лист № докум. Подп. Дата П40463 Лист 13 Подпись и дата DC1 Soyuz TMA Подпись и дата SM Progress M Progress M MRM2 Fig. 3.3 – ISS RS configuration consisting of SM, DC1, MRM2 and MRM1 Soyuz TMA FGB Инв. № дубл. MRM1 Взам. инв. № 3.4 ISS RS consisting of SM, MRM2, MRM1 and MLM Resources allocated to the MPF include: - allocated working volume of : up to 1 m3 on SM, up to 0.2 m3 on MRM2, up to 3 m3 on MRM1, and up to 8 m3 on MLM; - power supply: - on SM and DC1 up to 0.3 kW (daily average) and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation; - on MRM2 up to 0.1 kW (daily average); - on MRM1 up to 0.1 kW (daily average); - on MLM up to 1.0 kW (daily average) inside the pressurized cabin and up to 1.5 kW (daily average) outside the pressurized cabin; - heat rejection capacity: - on SM, DC1 and MRM2 up to 0.3 kW (daily average); - on MRM1 up to 0.1 kW (daily average); Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата - on MLM up to 1.0 kW (daily average) after deployment of an additional radiative heat exchanger; - the number of workstations on the outer surface: -4 pcs. on the SM (8 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account); -5 pcs. on MRM2 (7 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account); -9 pcs. on the MLM (13 pcs., when deliverable Multi-Purpose Workstations (MPWs) are taken into account); - payload data downlink capacity (maximum, via TM IU unit): up to 2 MB per a session; - ISS attitude control mode (nominal): Orbital Coordinate System (OCS); - ISS OCS attitude control accuracy : ± 10 angular minutes; - ISS angular rate stabilization accuracy: 0.005 deg/s; П40463 Изм. Лист № докум. Подп. Дата Лист 14 - the number of telemetered parameters: up to 212 (SM), up to 50 (MRM2), up to 36 (MRM1), up to 323 (MLM); - the list of electrical interfaces available for MPF: -RS-232; -RS-422 (on SM and MLM); -RS-485 (on SM and MLM); -Ethernet; -USB; -MIL STD 1553B (only on MLM); - HF with wave impedances of 75 Ohm and 50 Ohm (on SM and MLM); - discrete control commands (on SM, MRM2 and MLM); - the number of vaccumization interfaces for MPF: 1 pc on MRM2, 1 pc on MRM1, 2 pcs on MLM; - the number of thermostatting interfaces for MPF: 2 pcs. on MLM. - delivery of cargo to ISS RS onboard Progress M (M1) logistics spacecraft: on average up to 600 kg per year; - return from ISS RS of up to 110 kg of payloads per year. The external appearance of ISS RS in the above configuration is shown in the Figure Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The MPF cargo traffic to ISS RS is planned based on the following assumptions: П40463 Изм. Лист № докум. Подп. Дата Лист 15 Инв.№ подл. Изм. Лист № докум. Подп. Дата П40463 Лист 16 SM Взам. инв. № Soyuz TMA MLM Инв. № дубл. Подпись и дата FGB MRM2 Progress M Soyuz TMA MRM1 Fig. 3.4 – ISS RS configuration consisting of SM, MRM2, MRM1 and MLM Progress M Подпись и дата 3.5 Characteristics of communication links and downlinking The preliminary design calls for establishing on ISS RS intercomputer digital data exchange links with MCC-M via RF links of the standard SM systems – Telephone and Telegraph Communications System (TTCS), RF communications and control system (RF C&CS) Regul-OS, TV System (TVS) and onboard telemetry system OI TS 2-12 with data throughput of: - 1.2 kbps via the Telephone & Telegraph System Interface Unit (TTS IU) and the TTCS VHF link (up- and down-linking); - 2.4/4.8 kbps via interface units IU or TM IU and RF-link phone-2 of RF C&CS Regul OS (up- and down-linking); -16, 32, 64 kbps via interface units IU or TM IU and RF-link phone-3 of RF C&CS Regul OS (up- and down-linking); - 51.2/102.4 kbps via TM IU and RF-link of the OI TS 2-12 system (subsystem B) in the data array transmission mode (downlinking); Regul-OS when using Zveno-B hardware (up- and down-linking); Out of the abovementioned communications links, currently implemented onboard SM and available for digital data exchange are: - RF C&CS Regul OS RF-link phone-2 with 4.8 kps capacity (via IU unit); bandwidth, and for that reason is impractical for digital data transmission and is Подпись и дата Инв. № дубл. - the TTCS VHF link with 1.2 kbps capacity (via TTS IU unit); Взам. инв. № Подпись и дата - 16, 32, 64 kbps (altogether up to 96 kbps) via user channels ПГ 1,2 of RF C&CS - RF C&CS Regul OS RF-link phone-3 with 16 kps capacity (via IU unit). The TTCS VHF link is mostly used for communications with the crew, has a low assigned a backup status. Exchange of data at 4.8 kbps over the phone-2 channel of RF C&CS Regul OS via the flight model of IU makes it possible to downlink up to 100 KB of data during a 5minute communications session. Exchange of data at 16 kbps over the phone-3 channel of RF C&CS Regul OS in the Инв.№ подл. forward (uplink) channel is working normally, but the downlink, for the time being, П40463 Изм. Лист № докум. Подп. Дата Лист 17 provides no more than 150 KB of data over a 5-minute communications session. If larger files need to be downlinked, a series of several consecutive communication sessions can be used. Besides, as the next phase in its upgrade, there are plans to switch to (after proper testing is completed) 32 and 64 kbps transmission modes for the phone3 channel of Regul-OS. The maximum amount of payload data that can be downlinked via TM IU over telemetry channel per one communications session is 2 MB, with other users not being able to use this communications channel while the payload data are being downlinked. In early 2011, a Radio Data Transmission System (RDTS) is to be deployed on the SM of the ISS RS, which is to provide additional data downlink capacity: - RF-link with up to 100 Mbps throughput (downlink); - receiving data over HotLink from the payload installed on the outer surface of the SM for its direct transmission. The RDTS system allows downlinking no less than 3.7 GB of data during a 5-minute Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата communications session. П40463 Изм. Лист № докум. Подп. Дата Лист 18 3.6 Trajectory and navigation support for space experiments ISS, together with the ISS RS, is continuously (normally) operated in the orbital coordinate system. The accuracy and stability of maintaining the ISS in the OCS are: - ISS OCS attitude control accuracy : ± 10 angular minutes; - ISS angular rate stabilization accuracy: 0.005 deg/s Additional requirements for payload accuracy and stabilization during a program of experimental tests shall be met through the use of additional specialized (or multipurpose) equipment working in conjunction with the operating mission payload equipment. ISS can perform programmed pitch and roll maneuvers within ± 15 degrees (this constraint is imposed due to the lighting conditions of the thermal control system panels on the US orbital segment). Installed at present on one of the on-board crew support computers is the Sigma Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата program for displaying the trajectory and navigation flight environment, which makes it possible to perform the following tasks: - continuous real-time display on the screen of the space station position, current orbit track, coverage areas of the nearest ground stations, the start and end times of the next communications session with Earth, lighting environment in orbit, mission elapsed time, etc. Used to display the “running view” of the current location under the flight path are Earth surface maps of various scale: ranging from coarse (mapboard-type maps) to detailed (1:200000). As all the maps are bitmap images on cylindrical projection, it is also possible to use any other set of maps or color photos (prepared in the same format); - provide real-time simulations of the future (prediction) or the past position of the space station. Selected as variable simulation parameters can be year, month, day, hour and second of the flight, as well as the number of the orbit and the number of days into the mission. When the simulation is run “forward”, the latest available orbital data are Инв.№ подл. extrapolated, when the simulation is run “backwards”, the history of orbital and attitude П40463 Изм. Лист № докум. Подп. Дата Лист 19 data is used. There is a “fast-motion” mode for displaying the space station position. In addition to this, the space station position can be "frozen” in its orbital track on the screen at any desired moment in time. - review all the available electronic maps in the “geographic atlas" mode and determine geographic coordinates of any area on the Earth surface; - to automatically determine on the e-maps the names of a region, a country, a water area (i.e., a sea, a bay, a sound), or an area of the Russian Federation, which is being overflown by the space station, and output these data in a specified window on the display screen; - to promptly calculate (predict) when and how well a specified area on the Earth surface is going to be visible from the space station within the interval of time covering the next 16 orbits to a week. Coordinates of a region can be specified by means of an arbitrary point immediately on the screen itself (on the map) or selected from any preprepared list of objects. The trajectory and navigation support software includes lists on the following subjects: ecology, geology, etc. Selecting an item on these lists can be Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата done by typing the name of the desired item on the keyboard. The visibility can be calculated for several targets at the same time, with subsequently displaying the data on what targets are visible during the current orbit. Also calculated are the coverage areas of the specified ground stations; - to evaluate reliability (the level of likelihood) of detecting and identifying the known feature, a group of features or a sector of the terrain in the observed region taking into account geographic and meteorological observation conditions. The evaluation takes into consideration the presence of cloud cover (intensity on the scale of 0 to 10) over the region under observation. The cloud cover intensity is automatically evaluated based on monthly average values or is set manually based on real-time data. Evaluated automatically is also the number of observations which need to be planned in order to identify the desired feature with the specified level of reliability. - to simulate in real time a segment of the Earth surface and/or of the celestial sphere which is visible through the specified porthole. To simulate the celestial sphere, Pulkovo observatory catalog is used – 5050 brithest stars (recalculated for 2003 epoch); П40463 Изм. Лист № докум. Подп. Дата Лист 20 also continuously calculated are positions of the Sun (and solar reflection from the Earht surface), the Moon and planets, Other SC, for which orbital parameters are available. There is a mode for the automatic selection of that porthole, which is the best suited for observing the specified feature on the Earth surface or the celestial sphere. In addition to the actual portholes, there is a "virtual porthole”, which simulates the view forward (or backward) along the flight path. - to simulate the space station rotation in coordinates bound with the specified window. This makes it possible, even when there are no available data on the current attitude, to determine the actual attitude by manually bringing into coincidence the electronic model of the porthole and the actual image visible through the porthole, using in the process such visual cues as the horizon line, the Sun, the Moon and bright stars. to receive voice messages about various events (beginning and end of a communications session, orbital sunsets and sunrises, a new orbit, etc.). To assure normal operation of the trajectory and navigation support software, provisions have been made for daily uplinks of the orbital trajectory data predictions. to the space stations on removable hard disk drives onboard Soyuz TMA spacecraft. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата New versions of the software with the updates reflecting crew comments are delivered П40463 Изм. Лист № докум. Подп. Дата Лист 21 3.7. The list of photographic and video equipment onboard ISS RS Currently available onboard ISS RS is equipment (still photo/video cameras), which can support, within certain limits, the tasks of Earth remote sensing. Tables 3.7.1 and 3.7.2 provide the lists of photographic and video equipment onboard ISS RS, respectively. Table 3.7.1 The list of photographic equipment onboard ISS RS Major accessories Equipment name Still camera Nikon D2X Nikkor autofocus lenses Still camera Nikon D3 Nikkor autofocus lenses Still camera Nikon D3 Nikkor autofocus lenses Table 3.7.2 The list of video equipment onboard ISS RS Equipment name Major accessories Video system LIV Telescopic lens Подпись и дата Fujinon A16x9 BRM-28A HDTV videosystem Telescopic lens HJ15x8B IAS HDV videocamera The camcoder contains a high-resolution (Sony HVR-Z1 and Sony HVR-Z7) video camera with 3 CCD matrices and Video camera Sony DSR PD150P 12x zoom lens matches the 1/3-inch CCD system Optical stabilizer - Super SteadyShot™ A more detailed description, characteristics and external appearance of the above equipment are given in sections 3.8 and 3.9. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. HDV video recorder П40463 Изм. Лист № докум. Подп. Дата Лист 22 3.8. Equipment for still photography Specifications. Currently available onboard ISS RS are still cameras Nikon D2X, Nikon D3 and Nikon D3X (see Table 3.8.1.1), which make it possible to take highresolution photos of the Earth surface and other through ISS portholes, mostly portholes No.6, No.7 and No.8. The still cameras come with accessory lenses which are listed below and are intended for different tasks. Table 3.8.1.1 Russian photographic equipment onboard SM No Name . Designation Qty. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Still cameras 1 Still camera Nikon D3X SM-FOTO-D3X-U01 2 2 Still camera Nikon D3 SM-FOTO-D3-U01 №01 2 3 Still camera Nikon D2X SM-FOTO-D2X-U01 2 Lenses 1 Lens AF DX Nikkor 10.5 mm SM-FOTO-D1-U02-07 1 2 Lens AF-S Nikkor 14 mm SM-FOTO-D1X-U02-03 1 3 Lens AF-S Nikkor 17-35 mm SM-FOTO-D1X-U02-01 1 Lens AF-S Nikkor 17-55 mm SM-FOTO-D1-U02-06, 4 5 6 7 SM-FOTO-D200-U02 06 Lens AF-S Nikkor 28-70 mm SM-FOTO-D1X-U02-02 SM-FOTO-F5-1-U02 Lens AF-S Nikkor 80-200 mm Lens AF VR Zoom-Nikkor 80-400 mm f/4.5-5.6 № докум. Подп. Дата 2 SM-FOTO-D1X-U02-05 1 SM-FOTO-D3-U02 №2 1 П40463 Изм. Лист 2 Лист 23 8 SM-FOTO-D3X-U02-08 1 SM-FOTO-D200-U02-09 1 10 Lens Nikkor 14-24 mm SM-FOTO-D3X-U02-03 1 11 Telephoto lens AF-S Nikkor 600mm f/4 SM-FOTO-D3X-U02-07 1 12 Telephoto lens AF-S Nikkor 400mm f/2.8 SM-FOTO-D3X-U02-06 1 13 Telephoto lens Nikon TC-14E SM-FOTO-D3X-TC-14 1 14 Telephoto lens Nikon TC-20E SM-FOTO-D3X-TC-20 1 15 Telephoto lens Nikon TC-17E SM-FOTO-D3X-TC-17 1 9 Lens SIGMA AF 300-800 f/5.6 The lens for ultra close-up photography Micro-Nikkor f = 105 mm Flash lamps 1 Flash lamp Nikon SB-800 SM-FOTO-D2X-U03 2 1 2 Battery charger for camera Nikon D2X Battery charger for camera Nikon D200 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Battery chargers SM-FOTO-D2X-U05 1 SM-FOTO-D200-U05 1 Power supply units 1 Storage battery Nikon EN-EL4 SM-FOTO-D2X-U06 6 2 Storage battery Nikon EN-EL4a SM-FOTO-D2X-U06 2 SM-FOTO-D2X-01 1 Accessories 1 A cable for connecting to a Laptop computer П40463 Изм. Лист № докум. Подп. Дата Лист 24 2 Remote control cable SM-FOTO-D2X-02 3 3 Flash lamp synchronizer СФ-5У SM-FOTO-D1X-U08 2 SM-FOTO-D1X-U09 2 SM-FOTO-D1X-U10 2 Photographic equipment cleaning kit SM-FOTO-D1-U12 1 Battery handle for SM-FOTO-D200-U06-01 4 5 6 7 (for the bracket) PC CARD ADAPTER (PCMIA adapter) camera Nikon D200 MB-D200 Power supply units container SM-FOTO-D200-U04 2 9 Stereo adapter PENTAX SM-FOTO-D200-SA 1 11 Adapter ring for stereo adapter SM-FOTO-D200-SA-R 1 PENTAX A bracket for stereo imaging through a SM-FOTO-D200-BR 1 porthole Photographic equipment is self-contained and is not connected to the onboard power Инв. № дубл. Взам. инв. № supply line. Chargers for storage batteries of the Nikon camera are hooked up to connectors on the LIV video system. Table 3.8.1.2 Подпись и дата 1 8 10 Подпись и дата Adapter Still cameras specifications (Table 3.8.1.2) Digital still camera Nikon D2X CCD matrix dimensions - 23.7x15.7 mm Image size - 4288 x 2848 Light sensitivity - Equivalent to 100÷800 ISO speed Recording medium - Compact Flash and Microdrive Инв.№ подл. memory cards П40463 Изм. Лист № докум. Подп. Дата Лист 25 Compression - RAW (NEF) and JPEG formats. LCD display - 2.5-inch 232000 with adjusted lighting Lenses - Autofocus lenses Nikkor and SIGMA AF 300-800 f/5.6 Viewfinder field of view - 96% of the frame area Optical exposure - Automatic (software controlled with time of exposure or aperture having higher priority) and manual Optical exposure measuring area - Matrix centrally weighted spot measurement Exposure time range - 1/8.000÷30s Bracketing mode - 2-9 frames with incremental steps of Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 1/3, 1/2, 2/3 or 1 EV Synchronization with the flash - 5 modes Power - Li-Ion battery EN-EL4a (11.1V) Battery charger - SM-FOTO-D1X-U05 Digital still camera Nikon D3 (Nikon D3X) CCD matrix dimensions - 36.0x23.9 mm (35.9х24.0 mm) Image size - 4288x2848 (6048x4032) Light sensitivity - Equivalent to 200÷6400 ISO speed 25600 ISO (100÷1600) Recording medium - Compact Flash and Microdrive memory cards Compression - RAW (NEF) and JPEG formats. LCD display - 3-inch, with 920000 pixels, with adjusted brightness, 100% frame Инв.№ подл. coverage П40463 Изм. Лист № докум. Подп. Дата Лист 26 Lenses - Autofocus lenses Nikkor and SIGMA AF 300-800 f/5.6 Optical exposure - Automatic (software controlled with time of exposure or aperture having higher priority) and manual Optical exposure measuring area - Matrix centrally weighted spot measurement Exposure time range - 1/8000÷30s Bracketing mode - 2-9 frames with incremental steps of 1/3, 2/3 or 1 EV - 5 modes Power - Li-Ion battery EN-EL4a (11.1V) Dimensions - 159.5x157x87.5 mm Mass - 1.24 kg (1.22 kg) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Synchronization with the flash П40463 Изм. Лист № докум. Подп. Дата Лист 27 Additional characteristics, external appearance and purpose of the above cameras are Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата shown in Fig. 3.8.1.1, 3.8.1.2. Fig. 3.8.1.1 External view of still camera Nikon D3 (Nikon D3X) П40463 Изм. Лист № докум. Подп. Дата Лист 28 Подпись и дата Инв. № дубл. Взам. инв. № Подпись и дата Инв.№ подл. Fig. 3.8.1.2 External view of still camera Nikon D2 П40463 Изм. Лист № докум. Подп. Дата Лист 29 3.9. Video equipment 3.9.1 LIV system specification LIV system is based on professional equipment operating in analog format BETACAM SP. Fig. 3.9.1.1 shows the video camera included in this system, and Table 3.9.1.1 LIV system performance data for Earth imaging f rom the altitude of 400 km using the lens Fujinon A16x9 BRM-28A (the lens is currently onboard ISS RS). Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Fig. 3.9.1.1 Overall view of the LIV system video camera Table 3.9.1.1 LIV system specification Parameter Number of pixels in the CCD matrix Value 437664 (752x582) Focal distance (max.), mm 144 Field of view, deg. 3.3x2.38 The imaged area on the ground, km2 23.2х18.4 Resolution per 1 pixel, m 30.9 П40463 Изм. Лист № докум. Подп. Дата Лист 30 At present, the video system does not have the optics, which would meet the quality requirements for Earth imaging for the purposes of Earth Remote Sensisng. 3.9.2. HDTV video system Specifications. Table 3.9.2.1 list HDTV system performance data during Earth imaging from the altitude of 400 km using the lens HJ15x8B IAS (the lens is currently available onboard ISS RS). Table 3.9.2.1 The HDTV system specification Number of pixels in the CCD matrix 2033600 (1920x1080) Focal distance (max.), mm 120 240 (without (with extender) Field of view, deg. 4.6x2.6 2.3x1.3 The imaged area on the ground, km2 32x18.4 16x9.2 16.6 8.3 Resolution per 1 pixel, m consultation with the Japanese, it can be used as the ISS RS system equipment. Its equipment with respect to the LIV system (the resolution of the HDTV camera is 4 Инв.№ подл. Подпись и дата Инв. № дубл. The owner of the HDTV video system is NASDA, however, at present, after Взам. инв. № Подпись и дата extender) further use must be agreed with NASDA, with participation of Rosaviacosmos. From the technical standpoint, the HDTV video system is the next-generation video times that of the LIV camera). In addition to this, HDTV provides more color information about the scene, which is important during interpretation and analysis of the features on the ground. The overall view of the HDTV camera is given in Fig. 3.9.2.1. П40463 Изм. Лист № докум. Подп. Дата Лист 31 It should be noted that the filming results can only be returned to Earth on a recording medium (HD video cassettes). The existing capacities of the ISS RS RF-links do not support downlinking of the filming results. At present, the Russian side has neither the equipment for ground processing of the information, nor the capabilities to review and copy video materials obtained in the Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата course of the HDTV system operation. Fig. 3.9.2.1 Overall view of the HDTV camera 3.9.3 HDV video system. The HDV video system is intended for performing the following tasks: - video recording of the experiments - video filming inside the SM - video filming of the Earth The HDV equipment includes camcorders Sony HVR-Z1 and Sony HVR-Z7 of the HDV digital format. Using an adapter to the bracket LIV/106/20 the camcorders can be П40463 Изм. Лист № докум. Подп. Дата Лист 32 installed on the bracket in order to fasten them to the SM handrails. The HDV kit also includes a wide-angle attachment x0.8 Sony VCL-HG0872, Sony batteries NP-F970, a lamp Sony HVL-LBP, video cassettes Sony PHDVM-63DM, a set of cables and adapters. The list of equipment (Table 3.9.3.1) Table 3.9.3.1 № Name Designation Qty. 1. Camcorder Sony HVR-Z1 SM-HDV-U01 1 2. Camcorder Sony HVR-Z7 SM-HDV-U10 2 3. Lens Fujinon HAs18x7.6BRM 137mm SM-HDV-U11 1 4. Adapter ACM-17 SM-HDV-U12 1 5. Camera light Sony HVL-LBP SM-HDV-U14 2 6. Wide-angle attachment x0.8 Sony VCL- SM-HDV-U02 1 Camera bag SM-HDV-U07 1 8. Camera bag SM-HDV-U08 1 9. Battery Sony NP-F970 SM-HDV-U03 6 10. Video cassettes Sony PHDVM-63DM SM-HDV-U04 14 11. Memory card CF 16Gb SM-HDV-DCV 8 12. Video-audio cable (1.5m) SM-HDV-01 1 Взам. инв. № 13. Video-audio cable (1.5m) SM-HDV-10 1 14. Video cable (5 m) SM-HDV-02 1 15. Video cable (5 m) SM-HDV-03 1 16. Adapter RCA-BNC SM-HDV-04 1 17. Adapter BNC -BNC SM-HDV-05 1 18. Adapter BNC -BNC SM-HDV-06 1 Инв.№ подл. Инв. № дубл. 7. Подпись и дата Подпись и дата HG0872 П40463 Изм. Лист № докум. Подп. Дата Лист 33 № Name 19. Adapter to bracket LIV/106/20 Designation Qty. From LIV/106/20 to 1 LIV video camera 20. Adapter iLink for MRU SM-HDV-U15 1 21. Cable iLink 6р-4р (2m) SM-HDV-11 1 External appearance, characteristics and possible uses of the above video camera are given in Fig. 3.9.3. 3.9.4 Video camera Sony DSR PD150P External appearance, characteristics and possible uses of the above video camera are Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата given in Fig. 3.9.4. П40463 Изм. Лист № докум. Подп. Дата Лист 34 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист № докум. Подп. Дата П40463 Camcoder Sony HVR-Z1 contains a high-resolution video camera with 3 CCD matrices and HDV video recorder It can be installed onto a bracket for securing it to the SM handrails The camera can be equipped with a wide-angle attachment x0.8 Sony VCL-HG0872 The camcoder can work in PAL and NTSC systems, as well as in HDV, DV and DVCAM formats It is also possible to downlink video and audio signals via the switch of the LIV video complex HDV signals are compressed in MPEG2 format used in ground digital HDTV channels, as well as in Blu-ray disk recorders Viewfinder: Electronic (color).Combined 12x (optical) zoom lens The camcorder has a system of color filters and balance of white as well as an amplifier and an electronic shutter Possible use: - video recording the progress of the experiments within experimental setups - video recording inside SM to provide information to general public - video recording of Earth - video recording from Soyuz during re-docking operations; - backup capability for TV broadcasts when primary LIV system is unavailable or out of order 35 Лист Fig. 3.9.3 Video camera HDV (Sony HVR-Z1) Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист № докум. Подп. Дата П40463 Built-in portable LCD display for viewing the recordings The video camera uses Sony’s Memory Stick The camera image sensor has three 1/3-inch CCD matrixes with a total of 450 000 pixels Characteristics of the 12-x zoom lens match 1/3-inch CCD system The optical stabilizer is Super SteadyShot™, which uses independent determination of horizontal and vertical motion A prism system in front of the lens effectively compensates camcordershaking when filming without a tripod Black and white LCD viewfinder with 180 000 pixels provides horizontal resolution of 500 TVL, which simplifies manual focusing control Video data are recorded on cassettes. One cassette holds 40 minutes of recording Fig. 3.9.4 Video camera Sony DSR PD150P Лист 36 4 Capabilities supporting scientific equipment operation on ISS RS modules 4.1 Service module (СМ) The following interfaces with the module are used during integration of the scientific equipment into the SM: - mechanical interface; - electrical interfaces, including power interface, telemetry interface, data interfaces; - thermal interface; - vacuum interface (connection to external environment). The SM design provides for a number of areas for installing the scientific equipment in orbit, which have structural support for mechanical attachment and connections of the scientific equipment to the ISS support systems. Such areas outside the SM are: - the УРМ-Н1 workstation, located on the SM outer surface along plane III of the Подпись и дата Working Compartment 1 between frames 3, 4. Installed on the SM body on the transition plate 17КС.300Ю1573-0 as a mechanical device for fastening scientific equipment if a Passive Base Point (PBP) 27КСМ.152Ю7200-0. Scientific Equipment is installed by an operator during EVA onto PBP using an adapter, Подпись и дата Взам. инв. № Инв. № дубл. which includes an Active Base Point (ABP) 27КСМ.152Ю7100-0; - workstation УРМ-Н2 formed by a system of handrails 25x25 mm in crosssection on the body of the SM Working Compartment 2 between planes I and II in such a way that the normal to the line connecting the centers of cross-sections of the two central handrails is slanted at an angle of 47о from plane I towards plane II. The scientific equipment is fastened onto the handles with special locks; - each of the workstations УРМ-Н3 (УРМ-Н4) is formed by four threaded М12 holes with the base of 400×x200 mm, located in the payload fairing supports on the outer surface of the SM along planes II and IV between frames 8, 8а, respectively. Scientific equipment is installed using adapters; Инв.№ подл. - the Deliverable Multi-Purpose WorkStation (DMPWS) 17КС.600Ю 1501А-0 is installed on УРМ-Н3. DMPWS consists of a base 17КС.600Ю 1501А-100 with П40463 Изм. Лист № докум. Подп. Дата Лист 37 PBP and a platform 17КС.600Ю 1501А-200 with three passive parts of scientific equipment adapters 17КС.600Ю 1150А-0 and a mating device 27КСМ.152Ю 7110-0 for installation onto a PBP. Normals of the three passive adapters installed on the platform shall be aligned with axes ±YSM and +ZSM. Installed on the УРМ-Н4 under flight test conditions can be a deliverable workstation developed with the use of design solutions implemented in the design of the DMPWS. The following volumes are reserved for installation and connection of scientific equipment inside the pressurized cabin of the Service Module: - on the backside of panel 407 (УРМ4-3 zone) for scientific equipment with dimensions of up to 175x400x60 mm; - behind panel 305 (УРМ4-2 zone) for scientific equipment with dimensions up to 220x350x300 mm. The SM external appearance is shown in Figures 4.1.1 and 4.1.2. equipment are shown in Figures 4.1.3 and 4.1.4. SM interior view, locations of portholes, laptops and mission payloads are shown in Figures 4.1.5, 4.1.6 and 4.1.7. SM resources used for integration of scientific equipment are listed in Table 4.1.1. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата External multi-purpose workstations on the SM for installing units of scientific П40463 Изм. Лист № докум. Подп. Дата Лист 38 Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 39 Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Fig. 4.1.1 – SM external view Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 40 Подпись и дата Взам. инв. № Подпись и дата Fig. 4.1.2 – SM external view Инв. № дубл. Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 41 Подпись и дата MPW-N1 Инв. № дубл. MPW-N2 Подпись и дата MPW-N3 MPW-D Fig. 4.1.3 – External MPWS for installing scientic equipment units on SM Взам. инв. № Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 42 Взам. инв. № Инв. № дубл. Подпись и дата Fig. 4.1.4 – External MPWS for installing scientific equipment units on SM MPW-N4 MPW-D-4 Подпись и дата MPW-N3 MPW-D Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 43 Подпись и дата Laptop Подпись и дата 426 mm porthole 228 mm porthole Инв. № дубл. Fig. 4.1.5 – SM interior view (starboard) Взам. инв. № Onboard power outlets Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 44 Подпись и дата Multipurpose biotechnology thermostat 228 mm porthole Onboard power outlets Подпись и дата 426 mm porthole Laptop Инв. № дубл. Fig. 4.1.6 – SM interior view (port side) Cryogem-03 Взам. инв. № Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 45 Подпись и дата Инв. № дубл. Onboard power outlets Подпись и дата Fig. 4.1.7 – SM interior view (floor) Multipurpose biotechnology thermostat 228 mm porthole Взам. инв. № Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 46 Взам. инв. № Инв. № дубл. Подпись и дата Table 4.1.1 – SM resources for integration of scientific equipment Подпись и дата Deliverable Multipurpose Workstation Passive payload adapter 17КС.600Ю 1152А-0 Active payload adapter 17КС.600Ю 1151А-0 Payload adapter 17КС.600Ю1150А-0 Deliverable multipurpose workstation 17КС.600Ю 1501А-0 Platform with adapters 17КС.600Ю 1501А-210 Passive basepoint 27КСМ.152Ю 7200-0 Retaining plate (ФИ-21) 17КС.600Ю 1501А-450 Mating device Active Base Point 27КСМ.152Ю 7110-0 Base 17КС.600Ю 1501А-170 Retaining plate (ФИ-20) 17КС.600Ю 1501А-350 Инв. № дубл. Подпись и дата Fig. 4.1.8 – Deliverable multipurpose workstation Sample fields of view of scientific equipment installed on the SM multipurpose workstation are given in the following figures: - Fig. 4.1.9 – field of view of scientific equipment installed on the УРМ-Н1 (axis of sight aimed at zenith); - Fig. 4.1.10 – field of view of scientific equipment installed on the УРМ-Н3 (axis of sight pointed towards zenith); Инв.№ подл. Подпись и дата Взам. инв. № - Fig. 4.1.11 – field of view of scientific equipment installed on the УРМ-Н3 (axis of sight pointed towards nadir); - Fig. 4.1.12 – field of view of scientific equipment installed on the УРМ-Н4 (axis of sight pointed towards zenith); - Fig. 4.1.13 – field of view of scientific equipment installed on the УРМ-Н4 (axis of sight pointed towards nadir); П40463 Изм. Лист № докум. Подп. Дата Лист 47 Подпись и дата of sight aimed at zenith). Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. - Fig. 4.1.9 – field of view of scientific equipment installed on the УРМ-Н1 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 48 Подпись и дата of sight pointed at zenith) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. - Fig. 4.1.10 – field of view of scientific equipment installed on the УРМ-Н3 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 49 Подпись и дата of sight pointed at zenith) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. - Fig. 4.1.10 – field of view of scientific equipment installed on the УРМ-Н3 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 50 Подпись и дата of sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Fig. 4.1.11 – field of view of scientific equipment installed on the УРМ-Н3 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 51 Подпись и дата of sight pointed towards zenith) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. - Fig. 4.1.12 – field of view of scientific equipment installed on the УРМ-Н4 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 52 Подпись и дата of sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Fig. 4.1.13 – field of view of scientific equipment installed on the УРМ-Н4 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 53 4.2 Docking compartment No.1 (DC1) Special features that DC1 provides for conducting scientific experiments are: - capability to install hardware on the outer surface of MRM2 for observing the plane of the local horizon; - availability of a porthole with a capability to sight the hardware in the horizon plane; - capability to place hardware inside pressurized cabin for short periods of time for conducting space experiments and to store it only for the periods between EVAs; - on-board systems resources for scientific equipment on the external surface are mostly borrowed from the SM. On the DC1 external surface, possible areas for deploying payloads are: - magnetomechanical latches 77КСД.1940-100, located on the cylindrical part and on the central sphere. - passive base points 27КСМ.152Ю 7200-0 (2 pcs.) located on the cylindrical part - brackets 240ГК.А2200А-101 for the latch of the outboard workstation placed (4 pcs. each) on the flange of the exit hatches. Locations on DC1 of external multipurpose workstations based on electromechanical latches are shown in Fig.4.2.1. Locations on DC1 of payload equipment, windows and electrical outlets are shown in Fig.4.2.2. DC1 resources used for integration of scientific equipment are listed in Table 4.2.1. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата (used for accommodating cargo booms ГСтМ). П40463 Изм. Лист № докум. Подп. Дата Лист 54 Подпись и дата Инв. № дубл. Подпись и дата Изм. Лист № докум. Подп. Дата Fig. 4.2.1 – Locations of external MPWS on DC1 Electrical connector Micro-meteorid shield 2 Взам. инв. № Micro-meteorid shield 3 Инв.№ подл. П40463 Лист 55 Electrical connector Micro-meteorid shield 1 Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 56 Взам. инв. № Инв. № дубл. Onboard power outlet Подпись и дата 228 mm porthole Cryogem-03M Fig. 4.2.2 – Locations of payload equipment, portholes and outlets of the onboard power grid on DC1 228 mm porthole Подпись и дата Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 57 Подпись и дата Инв. № дубл. Подпись и дата Table 4.2.1 – DC1 resources for integration of scientific equipment Взам. инв. № 4.3 Mini Research Module 2 (MRM2) Characteristics: - launch mass, kg: 3670±50 kg; - pressurized volume, m3: 12,5; - storage volume for cargoes and scientific equipment, m3: 0,2; - in particular, for scientific equipment, m3: 0,1; - power for scientific equipment, kW: up to 0.1; - maximum daily average rejection of heat from the hardware included in the MPF through the air loop of the thermal control system: up to 0.1; - launch vehicle: Soyuz-FG MRM2 external appearance is shown in Fig. 4.3.1 Micrometeorid shield Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Advanced cargo boom (on the passive base point) Egress hatch (with a porthole) Deliverable MPWS (on the passive base point) Fig. 4.3.1 – MRM2 external appearance. П40463 Изм. Лист № докум. Подп. Дата Лист 58 Special features that MRM2 provides for conducting scientific experiments are: - capability to install hardware on the outer surface of MRM2 for observations of the upper hemisphere and the plane of the local horizon; - availability of a porthole with capability to sight the hardware in the horizon plane; - capability to place hardware inside pressurized cabin for short periods of time for conducting space experime nts and to store it only for the periods between EVAs; - on-board systems resources for scientific equipment on the external surface are Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата mostly borrowed from the SM. Fig. 4.3.2 – Characteristics of standard external workstation adapters for installing scientific equipment units. Location of external deliverable multi-purpose workstation on MRM2 and its configuration are shown in Fig.4.3.3. MRM2 resources used for integration of scientific equipment are listed in Table 4.3.1. П40463 Изм. Лист № докум. Подп. Дата Лист 59 SE2 SE-1 MPWS-D Ympw SE-3 Zmpw Xmpw Payload Basepoint 2-1 Payload Basepoint 2-2 Fig. 4.3.3 – Location of the external deliverable MPWS on MRM2 and its configuration Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Advanced cargo boom П40463 Изм. Лист № докум. Подп. Дата Лист 60 Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 61 Взам. инв. № Инв. № дубл. Подпись и дата Table 4.3.1 – MRM2 resources for integration of scientific equipment Подпись и дата Sample fields of view of scientific equipment installed on the MRM2 BPB multipurpose workstation are given in the following figures: - Fig. 4.3.4 – field of view of scientific equipment installed on the PBP (axis of sight aimed at zenith); - Fig. 4.3.5 – field of view of scientific equipment installed on the PBP2 (axis of Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата sight aimed at zenith); - Fig. 4.3.4 – field of view of scientific equipment installed on the PBP1 (axis of sight aimed at zenith); П40463 Изм. Лист № докум. Подп. Дата Лист 62 Подпись и дата sight aimed at zenith) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Fig. 4.3.5 – field of view of scientific equipment installed on the PBP2 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 63 In addition to MPW, structural elements (handrails) can also be used for scientific equipment integration on the outer surface of MRM2. Examples of scientific equipment installation on MRM2 handrails and fields of view for scientific equipment are shown in Figures 4.3.6, 4.3.7. Radiators on the USOS Radiators on the USOS Инв. № дубл. Подпись и дата FGB Инв.№ подл. Подпись и дата Взам. инв. № SM resupply spacecraft Fig. 4.3.6 – An example of scientific equipment installation on MRM2 handrails П40463 Изм. Лист № докум. Подп. Дата Лист 64 1B 2А 2B Fig. 4.3.7 – Fields of view of scientific equipment installed on MRM2 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 1А П40463 Изм. Лист № докум. Подп. Дата Лист 65 4.4 Mini Research Module 1 (MRM1) Characteristics: - launch mass, kg: 7900; - pressurized volume, m3: 17,4; - storage volume for cargoes and scientific equipment, m3: 5,0; - in particular, for scientific equipment, m3: 3.0; - power for scientific equipment, kW: up to 0.1; - maximum daily average rejection of heat from the hardware included in the MPF through the air loop of the thermal control system, kW: up to 0.1; - launch vehicle: Space Shuttle Orbiter. MRM1 external appearance is shown in Fig. 4.4.1 FRGF Radiative heat echanger Docking target Docking TV camera Инв. № дубл. Подпись и дата Airlock Инв.№ подл. Подпись и дата Взам. инв. № PVGF ERA elbow Active docking unit Fig. 4.4.1 – MRM1 external appearance. П40463 Изм. Лист № докум. Подп. Дата Лист 66 Included in the MRM1 MPF is the mission payload equipment necessary for providing onboard MRM1 an extended range of services in support of Russian and commercial experiments. Set up in the pressurized cabin are 5 multi-purpose workstations (MPWs) equipped with mechanical adapters and mission payload equipment: - modular shelves (up to 4 pcs.); - Glovebox-C hardware with retractable glove box shelf; - MBLTT thermostat; - MBHTT thermostat; - multipurpose vibration isolation platform MVIP. Назначение Slots for modular shelves Arch/frame Modular shelf frame Подпись и дата Pull-out shelf Payload attachment slots Handle Инв. № дубл. Взам. инв. № Подпись и дата Special bolts Velcro pads Fig 4.4.2 – Mechanical payload adapter. Key specifications: - maximum payload unit dimensions 600x400x600 mm; - maximum number of retractable shelf modules - 4 - payload attachment to shelf modules: - anchor bolt attachment; Инв.№ подл. - elastic fasteners; - Velcro fastener. П40463 Изм. Лист № докум. Подп. Дата Лист 67 Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 68 Подпись и дата Инв. № дубл. Подпись и дата Table 4.4.1 – Characteristics of mission support equipment onboard MRM1 Взам. инв. № Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 69 Взам. инв. № Инв. № дубл. Подпись и дата Table 4.4.2 – MRM1 resources available for SE integration Подпись и дата 4.5 Multipurpose laboratory module (MLM) Characteristics: - launch mass, kg: 20700 kg; - pressurized volume, m3: 70.0; - volume for scientific equipment, m3: 8,0; - power for scientific equipment, kW: - up to 1.0 kW (daily average) inside the pressurized cabin and up to 1.5 kW (daily average) outside the pressurized cabin; - maximum daily average rejection of heat from the hardware included in the MPF, kW: up to 1.0; - launch vehicle: Proton M LV. To support scientific equipment installation, MLM has provisions for: - installation of payloads inside pressurized cabin of MLM (16 internal multipurpose workstations) with the total volume of the accommodation areas of no less than 8 m3 (including a workstation equipped with a porthole for installing units of scientific equipment); Взам. инв. № Инв. № дубл. Подпись и дата - installation of no less than 12 simultaneous payloads outside the MLM pressurized cabin; - mechanical interfaces; - vacuum interfaces; - interfaces to provide thermostatic control for scientific equipment; - interfaces to supply scientific equipment with power from the MLM On-board Equipment Control System; - command and data interfaces between scientific equipment and the MLM Onboard Equipment Control System; - payload operating conditions in required modes when conducting space Инв.№ подл. Подпись и дата experiments; - storing original materials and obtained results. In addition to this, to support a long-term program of scientific and applied research, MLM provides the following equipment: - vibration isolation platform; П40463 Изм. Лист № докум. Подп. Дата Лист 70 - glove box; - thermostats. In order to minimize EVAs when installing scientific equipment on external workstations, the following robotic equipment is provided: - ERA robotic arm; - automatic airlock (AL). The MLM external appearance is shown in Figures 4.5.1 and 4.5.2. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата External view of the airlock is shown in Fig. 4.5.3. П40463 Изм. Лист № докум. Подп. Дата Лист 71 Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 72 Взам. инв. № Инв. № дубл. a cupola with a porthole MPW-N7 Подпись и дата Fig. 4.5.1 – MLM external appearance MPW-N3 (Passive restraint 3) MPW-N9 MPW-N5 Подпись и дата MPW-N4 (Passive restraint 4) Airlock MPW-N8 Lab Base Point 1 (for ERA) Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 73 Инв. № дубл. MPW-N8 Lab Base Point 2 (for ERA) Взам. инв. № Подпись и дата Fig. 4.5.2 – MLM external appearance MPW-N4 MPW-N1 (Passive restraint 1) Подпись и дата Airlock MPW-N6 MPW-N2 (Passive restraint 2) ERA Lab Base Point 3 (for ERA) For installing scientific equipment outside the MLM pressurized cabin, the following External Multi-Purpose Workstations (EMPWS) are provided: - EMPWS1, EMPWS2 based on a passive fastener 77КМЛ.810Ю2600-0 located outside the MLM instrumentation and cargo compartment-3 along Plane I. Installation of scientific equipment onto EMPWS1, EMPWS2 is effected by means of payload adapter 77КМЛ.600Ю2200-0; - EMPWS3 based on a passive fastener 77КМЛ.810Ю2600-0 located outside the MLM instrumentation and cargo compartment-3 between Plane II and III. Installation of scientific equipment onto EMPWS3 is effected by means of payload adapter 77КМЛ.600Ю2200-0; - EMPWS4 based on a passive fastener 77КМЛ.810Ю2600-0 located outside the airlock. Installation of scientific equipment onto EMPWS4 is effected by means of payload adapter 77КМЛ.600Ю2200-0; - EMPWS5 based on a passive base point 27КСМ.152Ю7200-0, located outside Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата the MLM instrumentation and cargo compartment-3 along Plane III. Used for installing scientific equipment onto EMPWS5 is a mating device ABP 27КСМ.152Ю7110-0. It is possible to install onto EMPWS5 a multipurpose platform 17КС.600Ю1501А-210 with active adapters 17КС.600Ю1151А-0, allowing simultaneous installation of three payloads. Used for installing scientific equipment onto the platform are passive payload adapters 17КС.600Ю1152А-0; - EMPWS6 based on a passive base point 27КСМ.152Ю7200-0, located outside the MLM instrumentation and cargo compartment-3 along Plane I. Used for installing scientific equipment onto EMPWS6 is a mating device ABP 27КСМ.152Ю7110-0. It is possible to install onto EMPWS6 a multipurpose platform 17КС.600Ю1501А-210 with active adapters 17КС.600Ю1151А-0, allowing simultaneous installation of three payloads. Used for installing scientific equipment onto the platform are passive payload adapters 17КС.600Ю1152А-0; П40463 Изм. Лист № докум. Подп. Дата Лист 74 - EMPWS7 based on a support 77КМЛ.600Ю1006-100 located outside the MLM pressurized adapter between Plane III and IV. Installation of scientific equipment onto EMPWS7 is effected by means of a base for installing the scientific equipment onto a support 77КМЛ.600Ю1006-200; - EMPWS8 based on a support 77КМЛ.600Ю1006-100 located outside the MLM instrumentation and cargo compartment 3 along Plane II. Installation of scientific equipment onto EMPWS8 is effected by means of a base for installing the scientific equipment onto a support 77КМЛ.600Ю1006-200; - EMPWS9 based on a support 77КМЛ.600Ю1006-100 located outside the MLM instrumentation and cargo compartment 3 along Plane IV. Installation of scientific equipment onto EMPWS9 is effected by means of a base for installing the scientific equipment onto a support 77КМЛ.600Ю1006-200; - EMPWS based on a passive fastener 77КМЛ.820Ю7360-0 located on the in-andout table of the airlock. Installation of scientific equipment onto EMPWS4 is Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата effected by means of payload adapter 77КМЛ.600Ю2200-0. The in-and-out table of the airlock also provides structural elements for securing payloads when conducting experiments in the extended position of the table. Sample fields of view of scientific equipment installed on the MLM multipurpose workstation are given in the following figures: - Fig. 4.5.3 – field of view of scientific equipment installed on the EMPWS1 (axis of sight pointed towards nadir); - Fig. 4.5.4 – field of view of scientific equipment installed on the EMPWS3 (axis of sight aimed at zenith); - Fig. 4.5.5 – field of view of scientific equipment installed on the EMPWS3 (axis of sight pointed towards nadir); - Fig. 4.5.6 – field of view of scientific equipment installed on the EMPWS4 (axis of sight aimed at zenith); - Fig. 4.5.7 – field of view of scientific equipment installed on the EMPWS5 (axis of sight pointed towards nadir). П40463 Изм. Лист № докум. Подп. Дата Лист 75 - Fig. 4.5.8 – field of view of scientific equipment installed on the EMPWS6 (axis of sight pointed towards nadir); - Fig. 4.5.9 – field of view of scientific equipment installed on the EMPWS7 (axis of sight aimed at zenith); - Fig. 4.5.10 – field of view of scientific equipment installed on the EMPWS8 (axis of sight pointed towards nadir); - Fig. 4.5.11 – field of view of scientific equipment installed on the EMPWS9 (axis Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата of sight pointed towards zenith); Fig. 4.5.3 – field of view of scientific equipment installed on the EMPWS1 (axis of Инв.№ подл. sight pointed towards nadir) П40463 Изм. Лист № докум. Подп. Дата Лист 76 Подпись и дата sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Fig. 4.5.4 – field of view of scientific equipment installed on the EMPWS2 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 77 Инв. № дубл. Подпись и дата sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Fig. 4.5.5 – field of view of scientific equipment installed on the EMPWS3 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 78 Инв. № дубл. Подпись и дата sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Fig. 4.5.6 – field of view of scientific equipment installed on the EMPWS4 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 79 Инв. № дубл. Подпись и дата sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Fig. 4.5.7 – field of view of scientific equipment installed on the EMPWS5 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 80 Инв. № дубл. Подпись и дата sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Fig. 4.5.8 – field of view of scientific equipment installed on the EMPWS6 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 81 Инв. № дубл. Подпись и дата sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Fig. 4.5.9 – field of view of scientific equipment installed on the EMPWS7 (axis of П40463 Изм. Лист № докум. Подп. Дата Лист 82 Подпись и дата of sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Fig. 4.5.10 – field of view of scientific equipment installed on the EMPWS8 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 83 Подпись и дата of sight pointed towards nadir) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Fig. 4.5.11 – field of view of scientific equipment installed on the EMPWS9 (axis П40463 Изм. Лист № докум. Подп. Дата Лист 84 Automatic airlock is intended for: - removing payloads from the MLM pressurized adapter and placing them on the outer surface of the space station; - receiving payloads from ERA robotic arm and moving them into the internal volume of the airlock and on to the MLM pressurized adapter; - conducting scientific experiments in the internal volume of the airlock; - conducting scientific experiments outside the airlock on the extended table and at a specially prepared station. Key specifications of the airlock: - airlock mass, kg: up to 1050; - maximum power consumption with a payload, kW: 1.5; - gas volume, m3: 2,1; - maximum payload mass on the payload handling device, kg: 150; - maximum payload dimensions, mm: 1200x500x500; - the number of vacuum pumping cycles during flight tests, - allowable internal pressure, kg/cm2: 1.- 3; - residual pressure after vacuum pumping, mm Hg: 10-4; External view of the airlock is shown in Fig. 4.5.3. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата no less than: 200; П40463 Изм. Лист № докум. Подп. Дата Лист 85 Изм. Лист № докум. Подпись и дата Инв. № дубл. Passive restraint Взам. инв. № Подп. Дата Supports Operator pad the body Modified passive docking unit FRGF grappling fixture Payload moving assembly Handrails Подпись и дата Fig. 4.5.3 – Airlock external appearance External cover assembly Инв.№ подл. П40463 Лист 86 Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 87 Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Инв.№ подл. П40463 Изм. Лист № докум. Подп. Дата Лист 88 Подпись и дата Инв. № дубл. Подпись и дата Table 4.5.2 – Characterisitics of external multi-purpose workstation adapters Взам. инв. № 5 Cargo certification One of the essential conditions for integrating scientific equipment into Russian spacecraft and ISS RS is to certify the scientific equipment. All the scientific equipment hardware delivered by Russian transportation spacecraft to ISS RS shall be certified for transportation/functioning onboard the spacecraft and use onboard ISS RS, that is, the hardware shall comply with the current requirements levied upon the hardware by the Russian spacecraft and ISS RS. All the activities on the implementation and verification of compliance with the current requirements for the scientific equipment and on proving its flightworthiness are subdivided into the following groups, which correspond to the step-by-step process of development, verification and certification of the scientific equipment: b) verification of the scientific equipment to check and confirm that requirements specified for the equipment have been met. Verification includes tests, calculations, analyses, etc. Requirements for hardware are given in paragraph 5.5.; compliance with the specified requirements; evaluation of hardware flight A Russian organization develops scientific equipment in accordance with Подпись и дата Инв. № дубл. c) analysis of verification results: verification of equipment characteristics Взам. инв. № Подпись и дата a) development of scientific equipment to meet the specified requirements; readiness; development and publication of certification documents. requirements of НА-99, a foreign organization follows contract requirements for conducting the space experiment. Scientific equipment certification is conducted in order to verify its following integral properties: - safety (strength, fire safety, electrical safety, toxicological safety, radiation safety, Инв.№ подл. etc.); П40463 Изм. Лист № докум. Подп. Дата Лист 89 - equipment compatibility with spacecraft and ISS RS systems; - equipment compliance with requirements in the Specifications. Depending on the specific kind of equipment, certification is performed as follows: - safety and compliance with the specified requirements are verified for all types of equipment; - equipment compatibility with the spacecraft and ISS RS systems are verified for the equipment that has interfaces (mechanical, electrical, software, telemetry) with the spacecraft and operating on-board the spacecraft. 5.1 Documents used in the course of certification 5.1.1 Documents used in certification of scientific equipment are defined in Russian technical standards documents used for the development of rocket and space technology products. Certification documents attesting to certification of an Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата individual piece of equipment are: - logbook, data sheet, label (hereinafter referred to as logbook) included in the accompanying documents; - flightworthiness statement; - safety certificate. 5.1.2 Logbook The logbook is intended for identifying a piece of equipment, recording its key characteristics, and contains a flightworthiness statement for that particular unit. The logbook is published for each piece of equipment by its manufacturer (vendor) in accordance with the current requirements for shop-floor documentation. In some particular cases (for example, for certain foreign-made equipment, purchased items), when there is no logbook meeting the established requirements, the organizational unit in charge of that item publishes a document Инв.№ подл. functionally similar to a logbook. П40463 Изм. Лист № докум. Подп. Дата Лист 90 5.1.3 Flightworthiness statement. Flightworthiness statement is intended as an assertion by the developer (supervisor) company (organizational unit) that the current requirements of the Specification or a document which replaces it (supplement to a contract, etc). The Statement shall attest to the completion of the scheduled developmental testing, to the fulfillment of the current requirements for scientific equipment, and contain a permission to fly the equipment. The Statement is the primary certification document published by the developer based on the results of a series of activities aimed at analyzing, developmental testing and confirmation of the scientific equipment readiness for flight/flight testing per requirements of Russian technical standards. The Statement is published for the scientific equipment for which a permission to fly is sought for the first time (newly developed or structurally modified equipment), and which is used under the Russian program of scientific and applied research. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The Statement’s scope shall cover the flight of scientific equipment inside a particular type of a transportation spacecraft and its use within an ISS RS module. 5.1.4 Safety Certificate The Certificate attests to the scientific equipment compliance with the current safety requirements. The Certificate is published based on the results of analysis of the equipment safety characteristics and measures taken to prevent hazardous situations. The results of such an analysis are presented in the form of a report (attachment to the certificate), which, together with the certificate constitute a single Safety Data Package (SDP). The safety certificate is published: - for scientific equipment of foreign organizations: for the phase of its transportation on a Russian spacecraft and for the phase of its use and storage onboard ISS RS; П40463 Изм. Лист № докум. Подп. Дата Лист 91 - for Russian scientific equipment: for the phase when it is used and stored onboard ISS RS, and the phase when it is transported onboard a foreign spacecraft. If the scientific equipment is a re-flight item for a particular phase (a certificate was published for an earlier successfully completed flight), safety certificate is not published for that item for that particular phase. 5.2 Scientific equipment tests 5.2.1 Generally, scientific equipment is subjected to the following kinds of tests: - qualification tests (QT); - acceptance tests (AT); - tests at checkout and testing facility within the flight model of the spacecraft/ISS RS module; - incoming inspection at the processing facility; - tests at the processing facility within the flight model of the spacecraft/ISS RS All the tests and operations to service and process the scientific equipment at RSC Energia and the processing facility are only conducted per RSC Energiaapproved instructions and under supervision of its responsible representatives. The equipment. qualification model of the equipment, which is not intended for operation, but Инв.№ подл. Подпись и дата Инв. № дубл. instructions shall contain all the information that is necessary to handle the Взам. инв. № Подпись и дата module; 5.2.2 Qualification tests are conducted by the equipment developer on the which is built per documentation for the flight model of the equipment. The prime task of qualification tests is to check the equipment against specification or contract requirements under exposure to environments which are as close to operational environments as possible, and, if need be, under heavier duty test modes. П40463 Изм. Лист № докум. Подп. Дата Лист 92 5.2.3 Acceptance tests are done to check the equipment against the requirements of the documentation approved by RSC Energia. The procedure for conducting acceptance tests is determined by the contract requirements. 5.2.4 Tests at the checkout and testing facility within the flight model of the spacecraft/ISS RS module are conducted in order to check mechanical, electrical and software interfaces between the equipment and the spacecraft/module. Interfaces with the spacecraft are checked in the course of spacecraft processing at the checkout and testing facility; interfaces with an ISS RS module are checked in the course of joint tests of scientific equipment with the electrical model of the module at the checkout and testing facility. Tests within the flight model of the spacecraft at checkout and testing facility and at the processing facility are conducted when interfaces are available by agreement with RSC Energia. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 5.2.5 Incoming inspection of the equipment at the processing facility is conducted per agreed procedure after its transportation to the processing facility. Incoming inspection operations include: - inspection of external appearance and a check for missing items; - equipment operational integrity check (if need be). 5.2.6 Program of qualification and acceptance tests Requirements for equipment tests are defined in ОСТ 92-5100-89 and SSP 50094. A typical list of tests and verification activities under the programs of qualification tests and acceptance tests of the equipment is given in Table 5.2.1. For each type of tests a test procedure is developed. П40463 Изм. Лист № докум. Подп. Дата Лист 93 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Table 5.2.1 Test type № докум. Verified requirements Test/verification Подп. 1. Check for missing items (subparagraph # in Qual. Section 6) test Requirements of design – + Checks delivery set for missing items and Дата documentation for the completeness of technical and operational scientific equipment documentation 2. Inspection of the external Requirements of design – appearance Note AT + The external appearance of the equipment is documentation for the checked against outline drawing, and it is scientific equipment checked whether logbooks and certificates are available and completely filled out 3. Dimensions check Requirements of design – П40463 hardware, scientific equipment mounting holes, mounting holes dimensions + documentation for the Requirements of design – documentation for the scientific equipment center-to-center distances + of Mass and center of mass position are checked against the developed outline drawings scientific equipment 5. Packing check To be checked are: outline dimensions of the documentation for the 4. Checking mass and position Requirements of design – of the center of gravity + Лист 94 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Verified requirements № докум. Test/verification 6. Safety review Test type (subparagraph # in Qual. Section 6) test 6.3 – Note AT + Safety analysis includes safety assessment in Подп. general Дата and specialized fields (strength, safety, etc.), as well as an integrated assessment materials safety, toxicological and radiation of the hardware safety, 7 Mechanical loads tests The tests are performed to check the strength of 7.1. Vibration + + load-bearing elements of the hardware that has 7.2. Shock loads + – a mechanical interface (rigid attachment) with 7.3. Linear accelerations р – the spacecraft/module, as well as, if need be, to П40463 check the functional integrity of the hardware. 6.1.3 for spacecraft 6.2.2 for ISS RS The tests shall be performed in transportation and working configurations of the hardware under the types of loading which correspond to these configurations (for example, in a bag/package fastened in a way similar to the standard attachment to the spacecraft). If the hardware was tested at levels different from those currently established, the issue of Лист 95 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Verified requirements № докум. Test/verification Test type (subparagraph # in Qual. Section 6) test AT Note extending the applicability of these results Подп. needs to be coordinated with RSC Energia. 8 Environmental tests Дата 8.1. Humidity 6.1.2.3 for spacecraft, + – be agreed with RSC Energia 6.2.1.5 for ISS RS 8.2 Temperature The accuracy of humidity measurements is to when 6.1.2.2 + - 6.1.2.2 for spacecraft + + delivered to the processing facility 8.3 Temperature in flight П40463 at lower/higher temperature 6.2.1.4 for ISS RS 8.4 Thermal cycle Requirements The tests (for thermal stability) are conducted of + – Subjected to the tests is scientific equipment specifications for the operating in unpressurized compartments under scientific equipment exposure to cyclically varying temperature Лист 96 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Verified requirements № докум. Test/verification 8.5 Acoustic noise Test type (subparagraph # in Qual. Section 6) test 6.1.3.3 for spacecraft + Note AT – Подп. 6.2.3.3 for ISS RS The tests are conducted if the equipment is considered critical with respect to acoustic noise exposure, as well as in the cases where Дата the root-mean-square value of the acoustic pressure on the hardware in the locations where it is installed in the spacecraft/module exceeds 130 dB 8.6 High/low pressure tests 6.1.2.4 for spacecraft + - The tests are conducted in order to check operational integrity of the equipment under 6.2.1.3 for ISS RS П40463 exposure to extreme pressure values 8.7 Pressure drop rate tests 6.1.2.4 for spacecraft + - Subjected to the tests is scientific equipment built in the form of a pressurized unit or a vented container used inside the descent vehicle or orbital module of Soyuz spacecraft. Pressure drop rate is 100 mm Hg/s 9 Radiation stability tests 6.1.2.5 for spacecraft + 6.2.6 for ISS RS – The test is run for the kinds of equipment that are radiation exposure critical Лист 97 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Verified requirements № докум. Test/verification 10 Leakage tests Test type (subparagraph # in Qual. Section 6) test Requirements of + Note AT + Subjected to the tests is the equipment that has Подп. specifications for the a pressurized volume (an enclosure, a vessel scientific equipment containing gas, liquid, test tubes with biological Дата samples, etc.). Before and after strength tests the equipment must be tested for leakage. Before filling, the flight unit must be tested for leakage. 11 Thermal vacuum test 6.1.2.2 for spacecraft + – П40463 6.2.1.4 for ISS RS Subjected to tests is the equipment that operates in open space in unpressurized compartments. It is recommended that the tests be combined with thermal stability tests (see paragraph 8.3) 12. A check of electric circuit Requirements of specifications and design documentation for the scientific equipment + + A check of electrical circuits continuity and isolation. Лист 98 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Verified requirements № докум. Test/verification (subparagraph # in Qual. Section 6) test 13 Insulation and insulation Подп. breakdown tests 6.1.4 for spacecraft, 14. Inrush current test 6.2.4 for ISS RS Дата 15. Power consumption check 16. Functional test Test type Requirements of Note AT + + – + – + + + Acceptance tests are performed at nominal specifications for the supply voltage, while qualification tests are scientific equipment performed at those extreme voltages to which the scientific equipment is most sensitive under given conditions П40463 17. EMC test 6.1.2.5 for spacecraft 6.2.6 for ISS RS + – Лист 99 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Verified requirements № докум. Test/verification Test type (subparagraph # in Qual. Section 6) test Note AT All flight units of self-contained power sources, Подп. except the ones of the “tablet” type are subject Дата recording to tests. The tests include: visual inspection, physical characteristics, taking measurements of storage voltage and operating voltage, leakage test, cycling 18. Tests of self-contained (charge/discharge). power supplies and chargers Tablet-type self-contained power sources are tested within operating equipment. П40463 Flight units of chargers are tested under normal operating conditions. Self-contained power sources and chargers that have passed the tests within the equipment are not subjected to tests within this scope. Лист 100 Инв.№ подл Подпись и дата Взам. инв. №Инв. № дубл. Подпись и дата Изм. Лист Notes: № докум. 1) Symbols: - "+" – this test must be conducted; - "р" – these requirements can be verified through calculation (analysis); Подп. - tests/checks are not conducted Дата 2) It is acceptable, with the agreement of RSC Energia, not to conduct certain types of tests specified in the table. In that case, the equipment compliance with the requirements shall be verified through analysis. П40463 Лист 101 6 Specifications for experimental equipment delivered to ISS 6.1 Specifications for equipment transported in Russian spacecraft Progress and Soyuz 6.1.1 General These requirements are applicable to all the cargoes delivered to ISS in Progress and Soyuz spacecraft, to all the waste and cargoes removed from the station for disposal inside Progress cargo compartment or Soyuz orbital module, as well as to cargoes returned to Earth inside Soyuz descent vehicle. The document contains requirements for all the phases of transportation and for the spacecraft ground processing phase. All the transported cargoes shall meet the requirements of the normal operating conditions described in this Section. In off-nominal situations, including depressurization, cargoes shall remain fire-and-explosion safe, nontoxic, leakproof (gases, liquids, biological samples) and preserve its mechanical integrity, meet Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата safety requirements for crew and spacecraft equipment. There are no requirements to assure cargo functioning after an off-nominal situation. In accordance with the conditions required onboard spacecraft for cargo delivery, all the cargoes are subdivided into: - active cargoes, which require for their transportation connections to the spacecraft onboard systems (power supply system, thermal control system, telemetry, etc.); - passive cargoes, which do not require for their transportation any connections to the spacecraft onboard systems. 6.1.2 Environmental conditions 6.1.2.1 Gas medium Composition of the gas medium inside Cargo Compartment, Descent Vehicle and Orbital Module (in volume percentages) through all the phases of free flight up to the docking with the space station: - oxygen − 21...40% (at partial pressure of 120...350 mm Hg); П40463 Изм. Лист № докум. Подп. Дата Лист 102 - carbon dioxide – up to 3%; - hydrogen – up to 2%; - helium – up to 0.01%; - nitrogen – the rest. Gas media composition in Cargo Compartment, Descent Vehicle and Orbital Module after docking with the space station and opening of the transfer hatches is the same as the composition of the atmosphere inside the space station pressurized cabin. Phase of the operation Temperature In production and storage rooms +5÷+30°C Ground transportation ±50°C Assembly and testing 0÷+40°C On the launch pad (for cargoes) 0÷+40°C Orbital flight - for cargoes, when the crew is not present 0÷+40°C - for cargoes, when the crew is present +18÷+25°C*) - for cargoes outside pressurized compartments from minus 150 to + 125оС After spacecraft landing (for cargoes) *) ±50°C − Temperature is allowed to rise up to +30°C and drop down to +10° for no more than 3 hours a day. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 6.1.2.2 Temperature П40463 Изм. Лист № докум. Подп. Дата Лист 103 6.1.2.3 Humidity (at temperature +20°C) Phase of operation Relative humidity In production and storage rooms 20...85% Transportation up to 90% Assembly and testing 20...80% On the launch pad (for cargoes) 20...85% Orbital flight (for cargoes, when the crew is not present) 20...80%*) Orbital flight (for cargoes, when the crew is present) 30...75% After descent vehicle landing (for cargoes) up to 98% *) − A rise up to 90% for as long as 3 hours a day is possible. 6.1.2.4 Pressure Absolute pressure of the gas medium inside pressurized compartments through mission phases it may vary within 450...970 mm Hg. The vacuum outside the spacecraft (in the cargo compartment of Progress spacecraft when conducting experiments requiring its depressurization, or when cargoes are located on the outer surface of the spacecraft) is at 10-3...10−8 mm Hg. In case of depressurization of the cargo compartment or the descent vehicle of Soyuz, the cargo may stay at a pressure as low as 10-6 mm Hg for as long as 10 hours. The maximum pressure drop rate is 100 mm Hg/s. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата all the phases of ground processing is the atmospheric pressure, and through all the П40463 Изм. Лист № докум. Подп. Дата Лист 104 6.1.2.5 Radiation exposure Radiation exposure requirements for Progress and Soyuz spacecraft are defined in SSP 50094, Subsection 3.6. To evaluate exposure to external radiation sources, the following values are assumed to characterize the protection: during Progress missions, for elements inside the compartment located near to the hull – 1 g/cm2, during Soyuz missions, inside compartments near the hull − 1g/cm2, and under the couches in the descent vehicle − 3 g/cm2. Radiation from the internal source inside the descent vehicle is a flux of gammaray photons with energies of up to 9.7 MeV. The dose rate does not exceed 0.1 rad/day at the distance of 0.6 meters from the source (the area under the couches). 6.1.3 Mechanical loads 6.1.3.1 Coordinate systems Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Ground transportation: X1 axis is parallel to the direction of transportation. Positive direction of the axis is against the transportation direction; Y1 axis is perpendicular to X1 axis. The positive direction of the axis is up; Z1 axis is perpendicular to axes X1, Y1 and completes the right-handed coordinate system. Orbital insertion and flight: X axis is the longitudinal axis of the vehicle. Positive direction is towards maximum loads during ascent (Attachment 2); Y axis is perpendicular to X axis; Z axis is perpendicular to axes X, Y and completes the right-handed coordinate system. The XYZ coordinate system is rotated around X axis by 135° with respect to X1 Y1 Z1 coordinate system. Descent vehicle reentry and landing: X axis – The positive direction is towards maximum loads; П40463 Изм. Лист № докум. Подп. Дата Лист 105 Y axis is perpendicular to X axis. The positive direction is towards maximum loads; Z axis is perpendicular to axes X, Y and completes the right-handed coordinate system. 6.1.3.2 Types of mechanical loads All types of loads can be grouped as follows: - shock loads of short duration occurring during transportation, launch vehicle and spacecraft engine firings and shutdowns, separation of the spacecraft from the launch vehicle, spacecraft separation during reentry, etc.; - vibration loads produced by acoustic and mechanical effects during operation of propulsion systems and atmospheric turbulence; - linear and low-frequency dynamic loads. Cargoes that are highly susceptible to shock and vibration loads shall be installed Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата on shock absorbers by the developer. 6.1.3.3 Loads 6.1.3.3.1 When the spacecraft is transported within the processing facility When the spacecraft is transported by rail within the processing facility, the operational loads are: - nх1= ±1.5; ny1= –1 ±0.25; nz1= ± 0.2; When lifted, carried and installed onto supports: − in horizontal position: nх1= ±0.1; ny1= – 1±0.5; nz1= ±0.1; − in vertical position: nх1= –1.5; ny1= ±0.1; nz1= ±0.1. 6.1.3.3.2 During ascent to orbit Operational values for linear loads for cargoes (without taking into account the low-frequency dynamic component) are: П40463 Изм. Лист № докум. Подп. Дата Лист 106 - along X axis – +4.3; - along Y,Z axes – ±1.5. Operating values for quasi-static loads (taking into account the low-frequency dynamic component) for payloads secured in transportation position, which do not have (with the effects of transportation fixtures taken into account) any normal modes within the frequency range of up to 30 Hz, or have normal modes in the said frequency range, while having a Q-factor for the cargo-fasteners system of no more than 10, are 7.15 in any of the three mutually perpendicular directions occurring non-simultaneously. Duration of exposure to linear and quasi-static loads: up to 600 s. Vibration loads in 3 mutually perpendicular directions in the form of sine vibration are given in Table 6, and, at frequencies above 20 Hz in the form of random vibration, are given in Table 5. Shock loads are in accordance with Table 1. Operational acoustic loads on the spacecraft: Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата - acoustic noise levels (total acoustic pressure) during ascent to orbit are: outside spacecraft – up to 145 dB. The acoustic noise spectrum inside the payload fairing of the launch vehicle is given in Table 7. Duration of exposure: 20÷30 s. - inside cargo compartment and the orbital module – up to 135 dB. The acoustic noise spectrum is given in Table 8. Qualification levels are presented, duration of exposure is 120 s. inside descent vehicle – up to 125 dB. 6.1.3.3.3 When Soyuz emergency rescue system (escape tower) operates (offnominal situation) Operational values for linear loads: a) during descent vehicle escape manuever: nх=+15, exposure duration is 5 s, П40463 Изм. Лист № докум. Подп. Дата Лист 107 nх=-8, exposure duration is 2 s, nz,y=± 13, 1 Hz vibration, t=30 s; b) during ballistic descent of the descent vehicle after launch vehicle failure: nх=+27, exposure duration is 9 s, ny=+5, exposure duration is 13 s, nz=±1, exposure duration is 6 s. Vibration loads in three mutually perpendicular directions, applied to the escaping part as random vibration per Table 5. Shock loads are in accordance with Table 4. Operational acoustic loads on the spacecraft Acoustic noise levels (total acoustic pressure) during operation of the emergency rescue system (operation time is 4 s) are: - outside the spacecraft – up to 160 dB; - inside the orbital module – up to 150 dB; Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата - inside the descent vehicle – up to 140 dB. 6.1.3.3.4 In orbital flight: 1) operating values for quasi-static loads (taking into account the low-frequency dynamic component) for payloads secured in transportation position, which do not have (with the effects of transportation fixtures taken into account) any normal modes within the frequency range of up to 30 Hz, or have normal modes in the said frequency range, while having a Q-factor for the cargo-fasteners system of no more than 10, are in longitudinal direction: nx=±0.3, in lateral direction: nx=±1.2, in transverse direction: nz=±1.2 (simultaneous exposure) for 12 minutes; 2) vibration loads for all spacecraft compartments in 3 mutually perpendicular directions in the form of sine vibration are given in Table 6.1.3.3.5.3, and, at frequencies above 20 Hz in the form of random vibration, are given in Table 6.1.3.3.5.2; 3) shock loads are given in Table 6.1.3.3.4.2; П40463 Изм. Лист № докум. Подп. Дата Лист 108 4) operational loads for dynamic loads during docking with ISS are given in Table 6.1.3.3.4.3. Table 6.1.3.3.4.1 In the X-axis direction In two other mutually Pulse duration, perpendicular directions ms Number of Load Number of impacts impacts 2 40 2 1-3 Load Descent 40 vehicle, orbital module and cargo Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата compartment П40463 Изм. Лист № докум. Подп. Дата Лист 109 Table 6.1.3.3.4.2 Loads in the X-axis direction Loads in two other mutually perpendicular directions Spacecraft Accelerat Numb Pulse Accelerat Numbe Pulse duration, compartment ion, (g) er of duration, (ms) ion, (g) r of (ms) s impac impacts ts Descent vehicle, 40 5 1-3 40 5 1-3 orbital module and cargo compartment Table 6.1.3.3.4.3 In two other mutually perpendicular directions The number Cycle Load The number Cycle of loading duration, of loading duration, (ms) cycles (ms) cycles ≤10 100÷1000 ±1,0±0,2 ≤10 100÷1000 Взам. инв. № Инв. № дубл. Подпись и дата Loads in the X-axis direction Load ±0,8 6.1.3.3.5 During Soyuz descent and landing 1) operational values for linear accelerations: a) normal descent of the descent vehicle (nominal conditions) nх= 0…+6, ny,z= 0±1, duration – 600 s, including nх=+6, exposure duration is 20 s; Инв.№ подл. Подпись и дата ny,z= ±1, exposure duration is 20 s; a) ballistic descent of the descent vehicle (off-nominal situation): nх= 0…+10, ny,z= 0±1 for 600 s, including nx= +10, exposure duration is 20 s; ny,z= ±1, exposure duration is 20 s; П40463 Изм. Лист № докум. Подп. Дата Лист 110 Variation of operating values of loads with time is approximated by a sine halfwave with half-period equal to the exposure duration; c) during parachute system operation: - during drogue chute operation n= +10 (in any direction), exposure duration is 10 s; - during main chute operation nx= +8, exposure duration is 15 s; ny,z= ±4, exposure duration is 15 s; - during re-hooking n= +5 (in any direction), exposure duration is 5 s; d) touch-down with failed soft-landing thrusters (off-nominal situation): at first impact nх= +100 (a deviation of loading direction of ±15° is possible), ny,z=50 (direction of loads in transverse plane is arbitrary). Variation of loads with time is approximated by a sine half-wave with halfperiod τ=20-30 ms; vehicle during reentry in the form of random and sine vibration in accordance with Tables 6.1.3.3.5.2, 6.1.3.3.5.3: 3) shock loads are in accordance with Table 6.1.3.3.5.1. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 2) vibration loads (in three mutually perpendicular directions) on the descent П40463 Изм. Лист № докум. Подп. Дата Лист 111 Table 6.1.3.3.5.1 Loads in two other mutually perpendicular directions Accelera Number Pulse Accelera Number Pulse tion, (g) of duration, tion, (g) of duration, impacts (ms) impacts (ms) 100 2 1-2 100 2 1-2 Loads in the X-axis direction Spacecraft compartment Descent vehicle (during escape tower 40 3 3-5 40 3 3-5 Descent vehicle 40 2 1-3 40 2 1-3 during cargo return 20 7 1-3 20 7 1-3 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата operation) П40463 Изм. Лист № докум. Подп. Дата Лист 112 Table 6.1.3.3.5.2 Spacecraf Mission t phases compart Exposure Frequency subranges, Hz duration, s ment 20-50 50100 100- 200- 500- 1000- 200 500 1000 2000 Vibration acceleration spectral density, g2/Hz Ascent to Orbital orbit module, 0,02 0,02 0,02- 0,05 0,05 0,05- 0,025- 0,025 0,013 0,02- 0,01- 0,01 0,005 120 cargo compart ment Descent 0,02 0,02 0,02 0,02 vehicle Подпись и дата Orbital 0,02 0,02- 0,008- 0,004- 0,008 0,004 0,002 0,004 0,004 0,004- 480 cargo compart ment, Инв. № дубл. Взам. инв. № 0,02 module, descent vehicle Orbital Orbital flight module, 0,004 0,004 0,004 600 0,002 cargo compart Подпись и дата Инв.№ подл. 0,02 120 ment Descent 0,004 vehicle 0,004 0,004 0,004- 0,01 0,01- 0,01 0,005 П40463 Изм. Лист № докум. Подп. Дата 600 Лист 113 Spacecraf Mission t phases compart Exposure Frequency subranges, Hz duration, s ment 20-50 50100 100- 200- 500- 1000- 200 500 1000 2000 Vibration acceleration spectral density, g2/Hz Descent Descent 0,004 0,004 0,004 vehicle Escape Descent 0,08- 0,2- tower vehicle 0,2 0,4 0,4 0,004- 0,01 0,01- 0,01 0,005 0,4- 0,16- 0,08- 0,16 0,08 0,04 600 10 operation Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Loads vary linearly with frequency within a subrange. П40463 Изм. Лист № докум. Подп. Дата Лист 114 Table 6.1.3.3.5.3 For all Exposure Frequency subrange, Hz spacecraft duration, s compartments Mission phases 5-25 25-200 200-800 800-1500 15002500 Vibration acceleration amplitude, g Ascent to orbit 1 1-3 3-5 5-8 8 300 Orbital flight 0,5 0,5 - 1 1-3 3-5 5-2 300 Descent − 0,5 - 1 1-3 3 3-2 100 2 - 10 10 - 15 15 - 10 10 - 5 10 Escape tower 1 - 2 operation Loads vary linearly with frequency within a subrange. Table 6.1.3.3.5.4 31,5 63 125 250 500 1000 2000 4000 120 118 2000 - 100 - Maximum root-mean-square level of acoustic pressure, dB 129 134 138,5 136 135 127 Table 6.1.3.3.5.5 Center frequency of the octave frequency subrange, Hz 31,5 63 125 250 500 1000 Maximum root-mean-square level of acoustic pressure, dB 119 119 130 131 129 119 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Center frequency of the octave frequency subrange, Hz П40463 Изм. Лист № докум. Подп. Дата Лист 115 6.1.3.3.6 Autonomous transportation of equipment and hardware For autonomous transportation of equipment and hardware by all types of transportation, the recommended accelerated test modes are given in Table 6.1.3.3.6. Table 6.1.3.3.6 The number Shock pulse Transportation vehicle Pulse duration, acceleratio axes ms n, g Total of impacts number of per minute impacts (no more than) X1 Y1 Z1 Number of impacts 9 750 2500 1750 5 to 10 5000 120 Strength analysis of deliverable cargoes, including their fasteners, is done based on design overloads defined as the product of operating overloads and the safety factor f. The same safety factors f are also taken into account during qualification tests. Minimal safety factors are set in accordance with Table 6.1.3.4. When the structure is exposed to a combination of forces for the loads increasing the strength margin, the safety factor is set at f=1. Loads increasing the strength margin are determined during strength analysis. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 6.1.3.4 Safety factors П40463 Изм. Лист № докум. Подп. Дата Лист 116 Table 6.1.3.4 Loads per paragraphs Value of safety factor f, no less than 6.1.3.3.1 1,5 6.1.3.3.2 1,4 6.1.3.3.3 1,3 6.1.3.3.4 2,0 6.1.3.3.5) a,b,c 1,5 6.1.3.3.5) d not specified In the course of strength analysis an additional coefficient K is introduced, which is a multiplier for the safety factor: - for fasteners (for example: bolts, screws taking into account a pre-torque) К = 1.25; - for critical fasteners having a complex geometric shape (for example: brackets, - when using materials having a high spread in strength properties or a significant anisotropy (for example: engineering plastics), К=1.2; 6.1.3.5. Vibration and acoustic tests least as high as those given in paragraph 6.1.3. vibration per Table 6. Инв.№ подл. Подпись и дата Инв. № дубл. 6.1.3.5.1 Vibration and shock qualification tests are conducted at levels that are at Взам. инв. № Подпись и дата fittings), К=1.25; 6.1.3.5.2 It is allowed to replace random vibration tests per Table 5 with sine 6.1.3.5.3 Operational acoustic loads applied to the spacecraft during qualification tests are increased by no less than 3 dB, and the exposure duration by no less than a factor of 4, but no less than 120 s). 6.1.3.5.4 G-load qualification tests are conducted taking into account safety factors per paragraph 6.1.3.4. П40463 Изм. Лист № докум. Подп. Дата Лист 117 6.1.3.6 Microgravity Active cargoes that operate continuously or in the microgravity mode shall meet the requirements for microgravity conditions specified in paragraph 6.2.3 6.1.4 Electrical conditions and requirements for electrical equipment Electrical conditions and requirements are given for active cargoes which require connection to the spacecraft onboard power system. Active cargoes are connected to the spacecraft onboard power system via fourpin connectors to outlets rated at 3A (Progress M1), 10A and 20A using a circuit breaker. 6.1.4.1 Onboard power system voltage The spacecraft onboard power system provides DC power at 27 +−74 V. 6.1.4.2 Bonding to protect against static electricity Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата In order to assure that all the conducting parts of the cargo and the spacecraft have the same electrical potential, all the electrically conductive structural elements need to be bonded, that is, have reliable electrical interconnections with contact resistance of no more than 2.5 mOhm. 6.1.4.3 Insulation resistance Insulation resistance of electrical circuits in active cargoes shall be no less than 20 MOhm at relative air humidity of 45...80% within the temperature range of +15...+35°C, and no less than 1 MOhm at relative air humidity of 95% and +20°C temperature. Insulation of primary current-carrying circuits from the device case and between any electrically isolated circuits shall be able to withstand a test voltage of 200 V (effective or DC voltage) for 1 s. П40463 Изм. Лист № докум. Подп. Дата Лист 118 6.1.4.4 Design features Design of high-voltage elements in active cargoes shall rule out any possibility of corona discharges and short-circuiting at low pressure inside compartments. All current-carrying elements in active cargoes having non-insulated electric conductors located in the air flow shall be securely protected against contact with small objects using airtight covers. 6.1.4.5 Noise immunity and electromagnetic compatibility Requirements for electrical and RF equipment to provide noise immunity and electromagnetic compatibility when exposed to inadvertent interference finding its way into the equipment in a typical noise environment are given in paragraph 6.2.4.2.. 6.1.5 Cargo labeling requirements The cargoes to be delivered or removed are to be labeled with onboard data Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата sheets and barcode labels, as well as photographed and filmed on video. Deliverable cargoes shall have onboard data sheets and barcodes to make them identifiable per requirements of paragraph 6.2.5. Barcode labeling is done by affixing special labels carrying a barcode duplicated in alphanumeric format. Barcode labels must not cover any existing inscriptions on the cargo. The locations for onboard data sheets and labels are determined by the developer or a person in charge of the cargo and are specified in its dimensional installation drawing. If the cargo is not subject to barcode labeling, a “barcode is not to be installed” entry shall be made in the dimensional installation drawing. Photographs of the delivered cargo are taken separately prior to installation on the spacecraft, as well as after its installation on the spacecraft. Deliverable cargoes are loaded into the spacecraft and checked for labeling per design documentation requirements. П40463 Изм. Лист № докум. Подп. Дата Лист 119 6.1.6 Requirements for cargo mechanical properties Mechanical properties shall be consistent with the cargo delivery and disposal conditions. The cargo shall be able to go through the spacecraft hatches. The cargoes to be delivered are loaded into Progress spacecraft through the hatch in the docking assembly (inside diameter of 800 mm) and through three loading hatches (inside diameter of 470 mm) in the cargo compartment. Inside diameter of the boarding hatch in the orbital module of Soyuz is 660 mm, the diameter of the manhole hatch in the Soyuz descent vehicle is 620 mm. The dimensions of the cargoes are determined during approval of the dimensional installation drawings for these cargoes. Cargoes to be delivered can be secured inside Progress and Soyuz by means of: - flanges and bolts; - bands and straps; - putting cargoes inside containers. Mass, dimensions, inertia properties of the cargoes to be delivered shall conform 6.1.7 Packing requirements The packing used in flight shall preserve cargo integrity during transportation and storage within the transportation spacecraft. The packing material used in flight shall comply with SSP50094 paragraph 4.3.4. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата to the outline drawings approved by the Russian side. П40463 Изм. Лист № докум. Подп. Дата Лист 120 6.2 Specifications for the equipment stored and operated onboard ISS RS 6.2.1 Medical and technical requirements for habitable environment 6.2.1.1 Atmospheric composition Maximum content of major components in the space station atmosphere in orbit (volume %): - nitrogen: up to 78 % (no more than 600 mm Hg); - oxygen: up to 24.8 % - carbon dioxide: up to 3 % - methane: up to 0.5 % - hydrogen: up to 2.0 % - helium: up to 0.01 % - water vapor: up to 3 % (up to relative humidity of 90 %). 6.2.1.2. Harmful trace contaminants content The maximum content of harmful trace contaminants shall comply with Table acceptable risk (the duration of a period within an expedition to orbit during which acceptable risk standards apply must be additionally defined). Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 6.2.1. Russian standards correspond to zero risk, US standards correspond to П40463 Изм. Лист № докум. Подп. Дата Лист 121 Table 6.2.1 Maximum acceptable content of harmful trace contaminants in the space station atmosphere Compound 1) Russian MAC values 2) US SMAC values 3) for for 360 days in orbit 180 days mg/m3 mg/m3 hydrogen 1600 340 methane 3300 380 pentane 10 590 (7 days) hexane 5 180 (7 days) heptane 10 200 (7 days) formaldehyde 0,05 0,05 acetaldehyde 1 4 aliphatic aldehydes 1 in orbit 4 to 8 0,02 0,03 methyl alcohol 0,2 9 ethyl alcohol 10,0 2000 2-propyl alcohol 1,5 150 Инв. № дубл. 1-butyl alcohol 0,8 40 acetone 2 50 Взам. инв. № 2-butanone 0,25 30 benzole 0.2 (180 days) 0,2 toluene 8 60 xylene 5 220 sterol 0,25 43 (7 days) isopropylbenzol 0,5 49 (7 days) furan 0,05 0,025 Инв.№ подл. Подпись и дата propionic aldehyde Подпись и дата (benzaldehyde) П40463 Изм. Лист № докум. Подп. Дата Лист 122 Compound 1) Russian MAC values 2) US SMAC values 3) for for 360 days in orbit 180 days mg/m3 mg/m3 ammonia 1 7 ethyl acetate 4 - carbon monoxide 5 10 polymethyl cyclosiloxane 0,2 9-15 dichloromethane 5 10 1,2-dichloroethane 0,5 1 Freon-218 150 85 in orbit 1) compounds are grouped into structural classes 2) Russian Maximum Allowable Concentrations (MAC) are stated in the national standard GOST Р 50804-95 3) US Maximum Allowable Concentrations (SMAC) are stated in the document Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата "Maximum Allowable Concentrations for individual contaminants in spacecraft atmosphere" (JSC 20584) 6.2.1.3. Atmospheric pressure The total nominal pressure onboard the space station is maintained within 734770 mm Hg, the minimal pressure is no less than 700 mm Hg. 6.2.1.4. Atmospheric temperature Atmospheric temperature: - in the living area - 18-28 оC; - in the instrumentation area - 10-40 оС (during manned missions) and 0-40 оС during unmanned missions. Temperature outside pressurized compartments (in open space): -150 to + 125оС 6.2.1.5. Humidity. Relative humidity: 30-70%, up to 95% for short periods of time (up to 3 hours per day). Dew-point temperature: 4.4-15.6 оC. П40463 Изм. Лист № докум. Подп. Дата Лист 123 6.2.1.6. Aerosol content. Aerosol content in the atmosphere: no more than 0.15 mg/m3 for particles ranging from 0.5 to 300 micron. 6.2.1.7. Medical and technical requirements for microbiological content. Requirements for the allowable number of microorganisms are given in Table 6.2.2. Table 6.2.2 Source Air Sampling time (colony- prior to flight Number of bacteria Number of fungi (no more (no more than) than) 300 50 in flight 100 100 prior to flight 5,0 0,1 in flight 100 1,0 forming units/m3) Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Internal surface (colonyforming units/m2) There should be present no pathogenic bacteria or fungi. 6.2.2 Mechanical loading conditions Equipment loading and microgravity conditions and requirements given below apply to the loads occurring during storage and operation of the equipment in orbit within ISS RS. Requirements for other operational phases are defined separately in accordance with the documentation currently in effect. In particular, conditions and requirements for launching with the use of Soyuz transportation spacecraft and П40463 Изм. Лист № докум. Подп. Дата Лист 124 Progress logistics spacecraft, and for returning cargo using Soyuz are given in Section 6.1 of this document. If the equipment meets the below requirements, it can be stored and operated (as far as mechanical loading conditions go) in any ISS RS module. If need be, mechanical loading modes for a specific piece of equipment can be updated to take into account its specific location on the ISS RS. 6.2.2.1 Loads 6.2.2.1.1 Vibration loading Vibration modes are specified by means of vibration acceleration amplitudes within the up to 20 Hz frequency range and vibration acceleration spectral density values in the frequency range above 20 Hz. For the up to 20 Hz frequency range the modes are listed in Table 6.2.3. Random vibration modes within the 20-2000 Hz frequency range are given in Table 6.2.4. The modes are specified for three mutually perpendicular directions. Modes listed in Table 6.2.3 and 6.2.4. do not Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата apply to the equipment located inside and outside propulsion compartments of spacecraft, SM and other modules, when propulsion systems located inside these compartments are operating. Mechanical loading modes for such equipment are specified separately in accordance with the documentation currently in effect. Table 6.2.3 Sine-wave vibration modes Frequency range, Hz Vibration acceleration Time of application in amplitude, g each direction, s 1-5 0,2-0,4 2400 5-10 0,4-0,5 1200 10-20 0,5 1200 Notes: 1. The modes listed in the table correspond to the qualification test levels. 2. Vibration acceleration values vary linearly between frequencies. 3. The time of application of vibration acceleration in frequency subranges is specified in the tests using the method of smooth variation of frequency. П40463 Изм. Лист № докум. Подп. Дата Лист 125 Table 6.2.4 Random vibration modes Frequency, Hz 20 50 100 200 Time of 500 1000 2000 each Vibration acceleration spectral density, g2/Hz 0,004 0,004 0,004 0,004 0,004 0,004 application in direction, s 0,002 2700 Notes: 1. The modes listed in the table correspond to the qualification test levels. 2. The values for spectral densities between the above frequencies vary linearly with logarithmic scale for frequency and spectral density. If need be, the above vibration modes for an individual piece of equipment can be updated to take into account its specific location on the ISS RS. 6.2.2.1.2 Dynamic and cyclic loading of the equipment during in-orbit storage and operation within ISS RS Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The structure of the equipment installed inside and outside the ISS RS modules shall be capable of withstanding inertial loads caused by forces acting on the ISS structure (contact forces from dockings and undockings of various spacecraft, forces generated by operation of control system effectors, as well as crew intravehicular and extravehicular activities). In addition to inertial loads, there are loads generated by forces directly applied by cosmonauts (astronauts). In addition to the above loads, the equipment installed on the outer surface of the modules is subjected to the following loads: jet plume impingement loads; loads produced by a crew tether (when the tether is fastened to the equipment). Inertial loads for the equipment are given in the form of operational linear and angular accelerations of the center of gravity and about the center of gravity of the equipment in the OXYZ coordinate systems, which are defined as follows: П40463 Изм. Лист № докум. Подп. Дата Лист 126 - SM: X axis of the OXYZ coordinate system is parallel to the XRS axis and is pointed in the same direction. Y axis is perpendicular to the X axis, is parallel to the YRS axis and is pointed in the same direction. Z axis completes the righthanded coordinate system; - DC1 (located on the –YSM docking port): XDC1 axis of the ODC1XDC1YDC1ZDC1 coordinate system is parallel to the YRS axis and is pointed in the opposite direction. YDC1 axis is perpendicular to the ХDC1 axis, is parallel to the ZRS axis and is pointed in the opposite direction. ZDC1 axis completes the right-handed coordinate system; MRM2 (located on the +YSM docking port): XMRM2 axis of the OMRM2XMRM2YMRM2ZMRM2 coordinate system is parallel to the YRS axis and is pointed in the same direction. YMRM2 axis is perpendicular to the ХMRM2 axis, is parallel to the ZRS axis and is pointed in the same direction. ZMRM2 axis completes the right-handed coordinate system; MLM: X axis of the OXYZ coordinate system is parallel to the YRS axis and is Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата pointed in the same direction. Y axis is perpendicular to the X axis, is parallel to the XRS axis and is pointed in the same direction. Z axis completes the righthanded coordinate system. The following notation is used: aX — acceleration in the X axis direction; aYZ — acceleration in any transverse plane parallel to the OYZ plane; εX — angular acceleration about X axis; εYZ — angular acceleration about any transverse axis, which lies in a plane parallel to the OYZ plane and goes through the X axis. Recommended stiffness of fasteners for installed equipment shall correspond to natural frequencies of no less than 20 Hz. Operational linear and angular accelerations of the center of gravity and about the center of gravity of the equipment located inside and outside ISS RS modules with rigid attachment at interface points to the ISS RS in 6 degrees of freedom П40463 Изм. Лист № докум. Подп. Дата Лист 127 (that is, having the natural frequency of the attachment ≥20 Hz taking into account the stiffness of the attachment point) are: aX = 4.5 m/s²; aYZ = 6.0 m/ s²; εX = 0.2 rad/ s²; εYZ = 0.7 rad/ s². For the equipment having a natural frequency of the attachment below 20 Hz, operational values of linear and angular accelerations can be as high as the following values: aX = 22.0 m/s²; aYZ = 16.0 m/s²; εX = 1.3 rad/s²; εYZ = 7.0 rad/s². When determining design loads, the safety factor shall be set equal to 2. If need be, these accelerations can be updated for an individual piece of equipment to take into account its specific attachment stiffness values, dynamic characteristics of the primary structure of the equipment and its location on the ISS RS structure. The structure of the equipment installed inside ISS RS modules in the crew transfer path, in addition to inertial loads (see paragraph 0.2) in accordance with the requirements of approved document SSP 41163 shall withstand operational Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата loads of 556 N (design value of 778 N) caused by the crew knocking directly against the equipment. The force shall be applicable in any direction to any spot on the equipment accessible to the crew. The structure of the equipment installed on the outer surface of the ISS RS in close proximity to the crew transfer path, in addition to inertial loads (see paragraph 0.2) in accordance with the requirements of approved document SSP 41163 shall withstand operational loads of 50 kgf (490.5 N) caused by the crew inadvertently knocking against the equipment. The force shall be applicable in any direction to any spot on the equipment accessible to the crew. In accordance with requirements of the approved document SSP41163, a structure on the equipment which may serve as an attachment point for the hook of a crew tether shall be capable of withstanding the design load of 200 kgf (1962 N) П40463 Изм. Лист № докум. Подп. Дата Лист 128 applied at the tether attachment point and acting in any direction accessible to the crew. In accordance with requirements of the approved document SSP 41163 the structure of the equipment installed on the ISS RS outer surface (with the exception of solar arrays and radiators), shall be capable of withstanding the folowing local operational pressures generated by the thruster jets: - normal pressure of 16.7 kgf/m²; - circumferential pressure of 3.91 kgf/m². The surface area to which these pressures are applied: up to 0.25 m2. When equipment is installed on solar arrays and radiators, the values for operational pressures are to be additionally defined. Safety factor for operational pressures generated by thruster jets is to be set equal to 2. Operational number of the equipment loading cycles in the orbital phase of the mission during docking, control system operation, as well as during intra- and operational life is 15 years, is to be set in accordance with Table 6.2.5. Table 6.2.5 Equipment cyclic loading spectrum Инв. № дубл. Подпись и дата extravehicular activities, for evaluating fatigue strength when the equipment Инв.№ подл. Подпись и дата Взам. инв. № Acceleration level, % Operational number of acceleration cycles 100—90 100 90—80 200 80—70 700 70—60 800 60—50 950 50—40 1 150 40—30 1 500 30—20 6,49E+6 20—15 1,40E+7 П40463 Изм. Лист № докум. Подп. Дата Лист 129 Acceleration level, % Operational number of acceleration cycles 15—10 3,17E+7 10—2,5 8,05E+7 In this case, the 100-percent loading level is to be assumed to be equal to the maximum loading level specified in paragraph 6.2.2.1.2. As the equipment operational life increases, the number of loading cycles rises in proportion to the increase in operational life. 6.2.3 Microgravity 6.2.3.1 Microgravity environment in RS modules In accordance with Basic Requirements for ISS RS 27КСМ.0000-0ПЗ1, during ISS microgravity flight modes, which, per specification SSP41163, shall be maintained for 180 days per year in continuous 30-day intervals, RS modules Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата provide the following microgravity environment: - quasi-static accelerations (frequencies <0.01 Hz) of no more than 4 microg. Quasi-static acceleration in excess of NASA requirements is due to a disadvantageous position of the RS research modules with respect to the ISS center of gravity; - root-mean-square vibration acceleration levels in 1/3-octave frequency subranges (averaged over time intervals of 100 s) do not exceed the levels shown in Fig.1. Higher levels at frequencies ranging from 0.8 Hz to 5 Hz are due to the operation of solar array actuators and US segment radiators (SARJ, TRRJ), crew exercise on treadmill and stationary bicycle; maximum amplitudes of transient accelerations caused by individual sources do not exceed 10000 micro-g along each axis. At frequencies of 10 Hz to 300 Hz requirements are met at distances of no less than 1 meter away from the most powerful sources of disturbance, which include, П40463 Изм. Лист № докум. Подп. Дата Лист 130 in particular, compressors (for example, in air-conditioning systems), electric pumps in the heating and cooling loops, toilet, control moment gyros. Requirements may be updated for specific equipment locations. 6.2.3.2 Requirements for the equipment to maintain microgravity conditions In order to comply with microgravity requirements for ISS RS and for ISS as a whole during microgravity modes of the ISS flight (180 days per year in periods stretching for 30 days each) every piece of equipment shall meet the following requirements: the equipment shall not produce quasi-stationary forces of more than 4 grams acting for long periods of time (exceeding 30 seconds); the equipment operation shall not cause accelerations with frequencies of up to 10 Hz: in ISS RS modules, that are in excess of 10% of the levels shown in Fig. 6.2.3.1; The operation of the equipment shall not cause accelerations with frequencies in 6.2.3.1 at the equipment attachment point; the operation of the equipment shall not cause non-stationary accelerations with amplitudes exceeding 1000 micro-g at the equipment attachment point. 6.2.3.3 Noise level limit requirements for the equipment During its operation no piece of equipment shall generate noise in excess of 55 dB at the distance of 1 m from the source. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата the range of 10 Hz to 300 Hz that are in excess of 10% of the levels shown in Fig. П40463 Изм. Лист № докум. Подп. Дата Лист 131 micro-g, 1/3-octave RMS value Frequencies, Hz Fig. 6.2.3.1 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 6.2.4 Electrical requirements 6.2.4.1 Basic requirements 6.2.4.1.1 On-board power supply Power is supplied to the equipment from a DC power source of the Electrical Power Supply (EPS) system of an ISS module at nominal voltage of 28.5+/-0.5 V across the EPS output terminals. Steady-state supply voltage at the hardware input lies within the 23-29 V range. The hardware shall operate normally when exposed to sudden changes in supply voltage by +/-4.5V with a frequency no higher than 1 Hz and duration of no less than 0.1 ms. In that case, the voltage at the hardware input shall remain within the 23-29 V range. The on-board automatic equipment of the module provides bipolar switching of the primary power supplied to the hardware, as well as protection of power lines against possible overcurrent loads and short-circuits in the cabling and hardware. П40463 Изм. Лист № докум. Подп. Дата Лист 132 To assure an optimal selection of elements for power switching, overload protection, and of power cabling parameters, the following inputs from the users are needed: the number of power feeders and their purpose; timeline for applying and removing power in each feeder under nominal and offnominal situations; characteristics of each power feeder, including: the nature of the load (resistive, inductive, capacitive); power consumption (watt, ampere) timelines for the equipment under all operational modes, taking into account possible input voltage variations within specified limits; parameters of possible inrush currents in transient modes, including inrush current amplitudes and their durations. Acceptable values for inrush currents and their durations are additionally specified in each individual case and are agreed during development of electrical Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата schematics for the equipment interfaces with the module control system. In general, inrush currents must not exceed the maximum steady-state operating current multiplied by a factor of five. In that case the duration of the current pulses must not exceed 20 ms when input power voltage varies within 23-29V. Primary power circuits of the equipment shall have conductive coupling with neither the case of the device, nor with the telemetry circuits. The equipment must remain operational in case a primary power bus inadvertently comes into contact with the device case. Loads (devices) having individual protected power feeders must not have any conductive coupling between themselves via the primary power plus buses (“+”). As a rule, each device must be powered via a separate connector. Its type and pin assignment are additionally defined during development of electrical schematic for interfaces between the device and the onboard automatic equipment. П40463 Изм. Лист № докум. Подп. Дата Лист 133 6.2.4.1.2 Electrical insulation resistance. Resistance of electrical insulation between primary power supply circuits (both positive and negative) and equipment case shall be: no less than 20 MOhm at relative humidity of (45…80) percent and ambient temperature of (+15…+35) deg.C. no less than 1 MOhm at relative humidity of 95+/-3 percent and ambient temperature of 20+/-5 deg.C. Insulation resistance measurements are taken at 30V DC. 6.2.4.1.3. Electric strength of the insulation. Resistance of insulation between primary power circuits (both positive and negative) and the case of the equipment, as well as between any electrically isolated circuits, shall comply with requirements for electrical insulation resistance after application to these circuits of a 200V test voltage (effective or constant value). The test voltage shall not exceed allowable test voltages for components used in Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата the equipment. 6.2.4.1.4 Requirements for data interfaces with the ISS RS systems The equipment, which has data interfaces with the ISS RS systems, shall be safe for the Russian hardware and control systems that are sharing the interfaces. The equipment to be used onboard RS, shall be classified by the presence of the following interfaces: - electrophysical interfaces, which determine parameters of interfacing with electrical circuits for data transmissions. Such an interface must be subjected to the following operations: device connectors shall be mated to the actual on-board cabling to check their wiring; electrical circuit parameters shall be measured in the actual onboard cabling and evaluated to make sure they lie within tolerances for data transmission lines (MIL STD1553B, ETHERNET, etc.) П40463 Изм. Лист № докум. Подп. Дата Лист 134 performance tests shall be run via connected interfaces per user’s manual for the device. - information and logic interfaces determining protocols for data transmissions in the network to which the new user is connected, and clearly defining its functions. To be checked are: logic functions of the device as a user of a data network (controller or slave device); the impossibility for the user to corrupt formats and data content in an interface unrelated to the user; correctness of the user response to the set of commands contained in the interface. - software interfaces between newly-added equipment and the user providing protection of RS systems against off-nominal situation. To be checked in such an interface (belonging, for example, to a laptop computer) are hardware protection against false and invalid commands and operator’s instructions. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The equipment shall be checked in real onboard environment in order to obtain actual measurement results from the flight model of the onboard cabling against the background of active operation mode of the onboard systems over applicable interfaces. In verifying compliance with data security requirements, a special emphasis should be placed on standard interchangeable components and storage medium containing installation or autorun software (cartridges, hard drives, floppy disks, etc.) The use of such elements onboard shall be tightly controlled and measures shall be in place to guard against their unauthorized use in the RS equipment. To be checked is whether the protection is in place against: unauthorized launch of software and its installation in RS computers; corruption of basic software of the RS equipment supporting control system operation. П40463 Изм. Лист № докум. Подп. Дата Лист 135 Protective/warning labeling must be made and applied to interchangeable components to limit the list of devices where these could be installed. 6.2.4.2. Electromagnetic compatibility 6.2.4.2.1 Electromagnetic interference generated by scientific equipment 6.2.4.2.1.1 Low-frequency noise Peak voltage values for low-frequency noise (Upeak), generated by equipment in the ±28V power supply circuits of the ISS RS modules shall not exceed the values given in Fig. 6.2.4.2-1. f [kHz] Fig. 6.2.4.2-1 – Low-frequency noise Where: f is the frequency (kHz) Measurement band shall be at least: 10 Hz in the range of 30 Hz to 1 kHz; 100 Hz in the range of 1 to 10 kHz. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Upeak[dBμV] П40463 Изм. Лист № докум. Подп. Дата Лист 136 6.2.4.2.1.2 RF noise Peak voltage values for RF noise shall not exceed values given in Fig.6.2.4.2-2. Upeak[dBμV] f [MHz] Fig. 6.2.4.2-2 – RF noise Measurement band shall be at least: 1 kHz in the range of 0.01 to 0.15 MHz. 10 kHz in the range of 0.15 to 30.0 MHz. 6.2.4.2.1.3 Electric field strength of radiated RF noise. Equipment installed onboard ISS RS shall not generate noise exceeding the limits specified in Fig. 6.2.4.2-3. Above 30 MHz, compliance with the limits shall be assured for both horizontally and vertically polarized waves. Epeak[dBμV/m] Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата 100 kHz in the range of 30 to 100 MHz. f [MHz] Fig. 6.2.4.2-3 – Electric field strength П40463 Изм. Лист № докум. Подп. Дата Лист 137 Measurement band shall be at least: 1 kHz in the range of 0.01 to 0.15 MHz; 10 kHz in the range of 0.15 to 30.0 MHz; 100 kHz in the range of 30 to 1000 MHz; 1 MHz above 1000 MHz. These requirements do not apply to RF noise generated by emissions from radio transmitter outputs. 6.2.4.2.2. Immunity of equipment to electromagnetic noise 6.2.4.2.2.1 Low-frequency noise Peak voltage values for low-frequency noise in the ±28V power supply circuits of the module are given in Fig. 6.2.4.2-4. Взам. инв. № Инв. № дубл. Подпись и дата Upeak[V] f [MHz] Fig. 6.2.4.2-4 – Low-frequency noise Инв.№ подл. Подпись и дата 6.2.4.2.2.2 Industrial RF noise Peak voltage values for industrial RF noise in the ±28V power supply circuits of the ISS RS modules are given in Fig. 6.2.4.2-5. П40463 Изм. Лист № докум. Подп. Дата Лист 138 Upeak[dBμV] f [MHz] Fig. 6.2.4.2-5 – Industrial RF noise 6.2.4.2.2.3 Pulse noise The effect of the pulse noise is characterized by the following parameters: - amplitude and duration of a test pulse are given in Tables 6.2.4.2-1 and 6.2.4.2-2; Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата - pulse edge durations are no more than 5% of the pulse duration; - pulse rate is 1 Hz for a period of 1 minute (or for a period of time needed to evaluate performance). Table 6.2.4.2-1 Characteristics of pulse noise between power buses Parameter Pulse Value duration, microseconds Pulse amplitude, V 100 300 500 + 15 + 15 + 10 + 10 – 15 – 15 – 10 – 10 Table 6.2.4.2-2 Characteristics of pulse noise between each of the power buses and the case Value Parameter Pulse duration, microseconds Инв.№ подл. 50 50 100 200 300 П40463 Изм. Лист № докум. Подп. Дата Лист 139 Pulse amplitude, V + 35 + 35 + 10 + 10 – 35 – 35 – 10 – 10 Peak values of electric field strength inside ISS RS modules are given in Fig. 6.2.4.2-6. Epeak[dBμV/m] Подпись и дата f [MHz] Fig. 6.2.4.2-6 – Electric field strength inside the module 6.2.4.2.2.4 Radiated RF noise outside ISS Инв. № дубл. Peak values of electric field strength outside ISS RS are given in Fig. 6.2.4.2-7. Инв.№ подл. Подпись и дата Взам. инв. № Epeak[dBμV/m] f [MHz] Fig. 6.2.4.2-7 – Electric field strength outside ISS RS П40463 Изм. Лист № докум. Подп. Дата Лист 140 Field strength may vary from 134 dBmicroV/m to the specified value depending on the device location. The radiated signal is modulated in amplitude with 1 kHz frequency and 50% depth of modulation. 6.2.4.2.3. Requirements for radio receivers, radio transmitters and AFD Specifications of radio receivers, radio transmitters and antennas meet the requirements of Radio Regulations and recommendations of International Radio Consultative Committee (IRCC). Specifications of radio receivers, radio transmitters and antennas are checked for compliance with the standards of Radio Regulations using procedures, which meet Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата the requirements of IRCC Recommendations. П40463 Изм. Лист № докум. Подп. Дата Лист 141 6.2.5. Labeling 6.2.5.1. Special labeling for ISS In addition to the labeling usually used by the equipment developer or vendor, alphanumeric and barcode labels must be applied. Equipment delivered in a package shall have the proper labeling on the package. 6.2.5.1.1 Alphanumeric labeling. Alphanumeric labeling in two languages, the types and methods of labeling, specifics of using Rusian and English are described in the joint standard SSP 50094 (Section 4.6.7). 6.2.5.1.2 Barcoding. In order to set up inventory accounting of every piece of equipment and cargo, both delivered to ISS RS, and returned/disposed of from the space station, the ISS Cargo Traffic and Inventory is used. Each item included into block-by-block list which is entered into and then stored in the information system ISS Cargo Traffic and Inventory. To automate the inventory keeping processes, barcoding is used; therefore, all the items intended for use onboard ISS shall have barcode labels of one of the sizes with different information content: - barcode only, also duplicated in numerical format, - name and barcode, duplicated in numerical format, - system designation, name and barcode, duplicated in numerical format. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата and into cargo traffic shall have a description following a pre-defined data set, П40463 Изм. Лист № докум. Подп. Дата Лист 142 6.2.6. Ionizing radiation 6.2.6.1 Integral energy spectra of electrons and protons in Earth radiation belts at solar maximum are given in Table 6.2.6-1. Table 6.2.6-1 Proton energy, Proton stream, MeV cm-2⋅day-1 MeV cm-2⋅day-1 0,04 1,5E+10 1,00 3,9E+06 0,10 9,1E+09 2,00 2,3E+06 0,30 1,5E+09 3,00 2,0E+06 0,50 4,4E+08 4,50 1,7E+06 1,00 1,2E+08 6,00 1,6E+06 1,50 5,7E+07 10,00 1,4E+06 2,00 2,6E+07 20,00 1,2E+06 3,00 4,8E+06 100,00 5,9E+05 4,00 6,9E+05 300,00 6,9E+04 5,00 6,9E+04 500,00 8,2E+03 5,40 2,2E+04 700,00 3,7E+02 Note – These data are used to evaluate integrity of materials and elements located outside ISS RS, for which radiation hardness parameters are specified in the form of spectral characteristics 6.2.6.2 Absorbed doses of space electrons and protons for materials and equipment located inside ISS RS per 1 year of flight tests for various values of mass thickness of a spherical shielding under exposure to omnidirectional irradiation (solid angle 4π) are listed in Table 6.2.6-2. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Electron energy, Electron stream, П40463 Изм. Лист № докум. Подп. Дата Лист 143 Table 6.2.6-2 Absorbed dose, rad/year Mass thickness, g/cm2 electrons protons total 3,0E-01 2,4E+03 9,3E+01 2,5E+03 5,0E-01 1,1E+03 7,5E+01 1,2E+03 7,0E-01 5,9E+02 6,9E+01 6,5E+02 1,0E+00 2,4E+02 6,2E+01 3,0E+02 2,0E+00 9,0E+00 4,9E+01 5,8E+01 3,0E+00 1,6E+00 4,3E+01 4,4E+01 5,0E+00 1,0E+00 3,4E+01 3,5E+01 1,0E+01 6,2E-01 2,3E+01 2,4E+01 6.2.6.3 Absorbed doses of space electrons and protons for materials and equipment installed outside ISS RS per 1 year of flight tests for various values of mass (solid angle 2π) are listed in Table 6.2.6-3. Table 6.2.6-3 Absorbed dose, rad/year protons total 1,0E-05 4,0E+05 3,1E+04 4,3E+05 1,0E-02 7,3E+04 2,3E+02 7,4E+04 5,0E-02 9,3E+03 7,2E+01 9,4E+03 7,0E-02 5,2E+03 6,1E+01 5,3E+03 1,0E-01 2,8E+03 5,2E+01 2,8E+03 2,0E-01 8,7E+02 3,9E+01 9,1E+02 5,0E-01 1,8E+02 2,8E+01 2,0E+02 Инв.№ подл. Подпись и дата thickness, g/cm2 electrons Инв. № дубл. Mass Взам. инв. № Подпись и дата thickness of a spherical shielding under exposure to unidirectional irradiation 6.2.6.4 All radiation doses shall be recalculated for the specified duration of flight tests of instruments and equipment assuming that they are proportional to the duration of flight tests. Dosage safety factor (with respect to the listed data or data П40463 Изм. Лист № докум. Подп. Дата Лист 144 obtained by recalculation for other operation life) for the developed (purchased) equipment shall be no less than 2. 6.2.6.5 In case the hardware is reused guaranteed in-orbit operation time is determined by taking into account the total planned duration of flight tests. 6.2.6.6 Ionizing radiation responsible for soft and hard failures in the ISS RS equipment is characterized by integral spectra of linear energy transfer for heavy charged particles and differential energy spectra for protons. Table 6.2.6-4 provides integral spectra of linear energy transfer for heavy charged particles. Table 6.2.6-4 Linear energy Linear energy transfer for the heavy charged particles source Galactic cosmic rays at solar Solar cosmic Solar cosmic MeV⋅cm2/mg minimum (flux averaged over an rays (total rays (peak orbit), particles/(cm2⋅days) flux), flux), particles/cm2 particles/(cm2⋅d Подпись и дата transfer Инв. № дубл. 7,1E+01 6,7E+04 4,2E+06 7,0E-01 5,5E+01 4,9E+04 2,4E+06 1,0E+00 4,0E+01 3,4E+04 1,3E+06 3,0E+00 1,2E+00 8,4E+03 1,9E+05 5,0E+00 5,1E-01 4,1E+03 7,5E+04 1,0E+01 1,4E-01 1,1E+03 1,5E+04 2,0E+01 2,7E-02 2,0E+02 2,1E+03 3,0E+01 1,7E-05 1,8E+00 1,4E+01 4,0E+01 9,8E-07 1,5E-01 1,7E-01 5,0E+01 4,1E-07 7,7E-02 7,7E-02 Инв.№ подл. Подпись и дата 5,0E-01 Взам. инв. № ays) П40463 Изм. Лист № докум. Подп. Дата Лист 145 Linear energy Linear energy transfer for the heavy charged particles source transfer Galactic cosmic rays at solar Solar cosmic Solar cosmic MeV⋅cm2/mg minimum (flux averaged over an rays (total rays (peak orbit), particles/(cm2⋅days) flux), flux), particles/cm2 particles/(cm2⋅d ays) 7,0E+01 7,5E-08 1,6E-02 1,6E-02 9,0E+01 6,0E-09 1,4E-03 1,4E-03 Table 6.2.6-5 provides differential energy spectra for protons. Table 6.2.6-5 Earth radiation belts at Earth radiation belts at Solar cosmic rays solar minimum (flux solar minimum (peak (peak flux), averaged over an orbit), flux at SAA), protons/(cm2⋅day⋅M protons/(cm2⋅day⋅MeV) protons/(cm2⋅days⋅MeV) eV) 30 2,0E+04 8,2E+05 3,5E+08 50 1,7E+04 1,1E+06 1,4E+08 Инв. № дубл. 70 1,4E+04 1,1E+06 6,6E+07 100 1,1E+04 8,4E+05 2,7E+07 140 6,9E+03 5,5E+05 1,1E+07 Взам. инв. № Differential energy spectra for proton sources 200 3,2E+03 2,6E+05 3,3E+06 400 3,9E+02 3,5E+04 2,6E+05 600 6,4E+01 4,8E+03 4,4E+04 Energy, Инв.№ подл. Подпись и дата Подпись и дата MeV П40463 Изм. Лист № докум. Подп. Дата Лист 146 6.2.7. Requirements for materials The below requirements apply to all materials listed in the full list of nonmetallic materials. The full list of nonmetallic materials, which are in contact with the pressurized cabin atmosphere, includes: - structural materials used in fabrication of casings; - fasteners, circuit boards, covers, sheathes, etc.; - varnishes, paints, compounds, adhesives; - insulating materials for wires, cables, harnesses. The list has the official document status and must be signed by a responsible representative of the international partner. 6.2.7.1. Materials fire safety Materials shall not be capable of spontaneous ignition. Materials shall not be capable of maintaining combustion either on their own or Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата when integrated into another product or system. Fire-prevention measures - all the circuit boards shall be covered on both sides with silicon or another approved material, if they are not completely enclosed in a metal container and if they are not otherwise accepted by the Russian side; - all transformers or coils are fully enclosed in a metallic material or an approved potting compound. Exceptions from this rule must be specifically approved by the Russian side; - all the wires are covered with Teflon, all wires and cables are protected or routed in such a way as to rule out any possibility of wire damage which may cause sparks or short-circuits; - circuit protection shall be provided in order to avoid possible circuit overheating in off-nominal situations (for example, short circuit, as a result of an abrupt change or a delay); П40463 Изм. Лист № докум. Подп. Дата Лист 147 - insulation of power cables shall be heat resistant; connectors that do not have such protection shall be shielded with housings made of nonflammable materials. 6.2.7.2. Materials toxicity It is forbidden to use for the hardware structure any toxic or hazardous materials which may release gases detrimental to the crew in concentrations dangerous to the crew. Materials of the equipment located on the outer surface of ISS shall meet the standards for outgassing in vacuum with respect to loss of mass (no more than 1%) and the amount of condensing substances (no more than 0.1%), determined per GOST Р50109-92 or another standard similar to ASTME595. 6.2.7.3 Microbiological stability of the materials Equipment destruction to a limit posing a threat to health and life is not allowed. Microbial resistance must be specified for each listed material. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Equipment and its container must be disinfected at the launch site, unless otherwise specified by the Russian side. Usual methods of hardware disinfection include the use of liquid hydrogen peroxide and radiation. This usual processing applies to all external surfaces. This method can be revised if there is any danger of damaging the hardware. Disinfectant resistance shall be specified for each listed material. 6.2.7.4 Aging of materials An estimate of the equipment susceptibility to ageing shall be made by means of non-metallic materials analysis. Assessed on a regular basis shall be devices intended for multiple use in flight, as well as items and materials, which are used as samples as defined by the Russian side. Periods of time during which the properties of the materials remain preserved shall be specified for each listed material. П40463 Изм. Лист № докум. Подп. Дата Лист 148 6.2.8 Protection against static electricity 6.2.8.1 Protection of electronic equipment against static electricity during its installation and hookup to onboard cables shall be provided by taking the following measures: - bonding the equipment, that is, providing a secure electrical connection between the cases of the devices and the body of the ISS RS modules; - removing static electricity from the operator during electronic equipment installation using an antistatic wristband connected to grounding points available in the ISS RS modules. - removing static electricity from onboard cables during their connection to electronic equipment by using a multipurpose device 17КС.300Ю9052-0. 6.2.8.2 Hardware bonding is provided by means of bonding straps, equipped with which must be casings of the devices to be installed inside pressurized compartments. and to the body of the pressurized compartment by means of a fastener (a screw), or by mating disconnectable bonding straps. It is acceptable to bond devices via an electrical interface with the ISS RS onboard systems, where one of the electrical circuits which has galvanic coupling with the pressurized compartment body is assigned to serve as a bonding wire. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата The bonding is established by connecting a bonding strap to the device casing П40463 Изм. Лист № докум. Подп. Дата Лист 149 6.3 Safety requirements 6.3.1 General requirements 6.3.1.1 General requirements are applicable to SE design and development and are aimed at assuring the required level of SE safety both for the crew and for other hardware on the vehicle. 6.3.1.2 During its operation and storage the SE shall not crate dangerous situations or the risk of such situations occurring shall be minimized. The dangerous situations, as applied to SE, are classified according to the hazard level as follows: - Critical Hazard. The hazard which, if it occurs, may result in such damage to the vehicle equipment as does not preclude its further operation, or in a nondisabling injury to the crew, or in the need to use unplanned procedures, which affect the operation of onboard systems of the Russian spacecraft; - Catastrophic Hazard. The hazard which, if it occurs, may result in the loss of the 6.3.1.3 Development of SE and its utilization operations shall meet the following 6.3.1.3.1 Tolerance to failures resulting in dangerous situations operator error can result in a catastrophic hazard; Инв.№ подл. Подпись и дата Инв. № дубл. requirements in order to minimize the risk of occurrence of hazardous situations. Взам. инв. № Подпись и дата vehicle or in a disabling or fatal injury to the crew. SE shall be designed in such a way that: - no combination of two failures or two operator errors, or one failure and one - no single failure or single operator error can result in a critical hazard. 6.3.1.3.2 Design for Minimum Risk This requirement consists in assuring/selecting the necessary safety factors, scope of developmental and verification tests to assure high strength properties, survivability, resistance to various kinds of loads. Safety factors and scopes of testing are determined by standards depending on the types of equipment and П40463 Изм. Лист № докум. Подп. Дата Лист 150 specifics of its use. Typical examples of the use of the design for minimum risk are selection of safety factors, of safety margins when analyzing the structural strength of the body of sealed pressurized vessels, of load-bearing structural elements. 6.3.1.3.3 Safety taking into account vehicle/ISS services 6.3.1.3.3 Safety without taking into account vehicle/ISS services SE shall be capable of taking care of its safety by itself without any servicing on the part of the vehicle/ISS even in case of a contingency onboard the vehicle/ISS. 6.3.1.3.3.2 Safe With Vehicle Services If requirements of safety without servicing (paragraphs 6.3.1.3.3.1 or 6.3.1.3.3.2) are difficult to implement for technical reasons, the requirement of safety with servicing on the part of the vehicle must be met. In this case the overall safety of the SE together with the vehicle equipment that Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата is being used shall meet the requirements of paragraph 6.3.1.3.1 or 6.3.1.3.2 of this document with respect to hazardous situations. 6.3.1.3.4 Hazardous functions control 6.3.1.3.4.1 A function, which, if inadvertently triggered, may result in a critical hazard, shall have two independent inhibits for the entire time while the likelihood of this hazard exists. In those cases where the loss of function may result in a critical hazard no single failure shall result in the loss of this function. 6.3.1.3.4.2 A function, which, if inadvertently triggered, may result in a catastrophic hazard, shall have at least three independent inhibits for the entire time while the likelihood of this hazard exists. There shall be a capability to monitor the status of at least two of the three required inhibits . In those cases where the loss of function may result in a catastrophic hazard no two failures shall result in the loss of this function. П40463 Изм. Лист № докум. Подп. Дата Лист 151 6.3.1.3.5 Caution and warning devices In those cases where the occurrence of a hazardous situation requires urgent action on the part of the crew (fire, depressurization, toxic release, etc.), devices shall be used for providing a timely warning to the crew about these hazardous situations and/or for switching off the SE (system hardware). 6.3.1.3.6 Special procedures Procedures supporting the SE safety shall contain: Safety instructions for equipment handling, procedures to be followed in case of possible SE failures. 6.3.2 Design requirements 6.3.2.1 Materials Materials used in SE structure, including packaging, shall meet the following safety requirements. a) Toxicity The materials in use that are in contact with the spacecraft environment shall not Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата release into the environment any toxic and noxious chemical substances in concentrations constituting a threat to the life of the crew and spacecraft operation. Care must be taken to avoid the use in the SE hardware of any chemical substances which do not come into direct contact with the environment, but may pose toxicity threat if they leak into the spacecraft atmosphere (for example, may cause crew skin or eye irritation or affect spacecraft equipment). If, nevertheless, they need to be used, requirements of paragraph 6.3.1.3 shall be met in accordance with the hazard level. b) Fire safety Materials used under normal operating conditions and in case of cabin depressurization: shall not become a source of fire or explosion; shall be heat-resistant and shall not sustain combustion neither by themselves, nor when used within hardware assemblies and systems; shall not release flammable gases and form combustible or explosive mixtures. П40463 Изм. Лист № докум. Подп. Дата Лист 152 c) Microbiological safety The materials in use shall not be a source of microbiological contamination of the spacecraft atmosphere and structural elements, and shall not create a propitious environment for microorganism development, and shall be resistant to biodegradation. d) Operation in vacuum SE located outside the pressurized cabin of the spacecraft shall be resistant to exposure to heat and vacuum and shall not be a source of contamination of the space around and inside the module under normal environmental conditions. Non-metallic materials, as well as coatings used for sealing and insulating electrical circuits shall be tested for mass loss and volatile matter content under exposure to heat and vacuum and have mass loss of no more than 1% and volatile matter content of no more than 0.1%. Thermooptical properties of the surfaces of the SE located outside the pressurized cabin of the vehicle shall not affect the vehicle safety: exceed the Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата allowable thermal conditions, as well as create glare or flood exposure of lightsensitive elements of the vehicle. 6.3.2.2 Structure 6.3.2.2.1 SE structure shall be designed taking into account actual loads and safety factors accepted for the vehicle. 6.3.2.2.2 Materials used for the SE structural elements, including fasteners, shall be reviewed for corrosion cracking under stress (fatigue strength). As far as possible, alloys with high resistance against stress corrosion cracking shall be used. 6.3.2.2.3 SE structure shall be designed for maximum differential pressure occurring during ascent, descent or activities involving emergency depressurization and subsequent re-pressurization of the vehicle/ISS. The vents in the vented compartments shall have such surface areas as to assure structural integrity while providing the maximum rate of change for the pressure. П40463 Изм. Лист № докум. Подп. Дата Лист 153 6.3.2.2.4 Open surfaces on SE shall be smooth and have no burrs. 6.3.2.2.5 The structure of the SE and the packing used in flight shall have no breakable materials or shall preclude fragments of such materials spreading beyond casings or packing of the SE hardware in case of failures both under normal environmental conditions and in case of cabin depressurization. 6.3.2.3 Electrical safety SE electrical circuits shall be protected against possible overloads and shortcircuits (and potential ignition) by correct choice of wire gauge, wire insulation, circuit breakers, etc., etc. There shall be no electrical contact between the vehicle body and electrical circuits of the SE. SE hardware shall be designed in such a way as to protect the crew against an inadvertent contact with electrical circuits. In case the SE uses voltages above 30 catastrophic hazard level. Leak current during contact with the SE being serviced shall not exceed 0.07 mA DC for a normal contact with a human being. shall have a voltage difference exceeding 40 mV at frequencies of 1000 Hz or 6.3.2.4 Radiation safety Инв.№ подл. Подпись и дата Инв. № дубл. No two electrically conductive surfaces within the reach of a member of the crew Взам. инв. № Подпись и дата V, measures shall be taken to protect the crew against electric shock per lower, measured across the resistance of 1000 Ohm. All the SE elements which produce ionizing radiation shall be identified and their use shall be the subject of a special discussion and agreement with RSC Energia. 6.3.2.5 Living space safety SE shall not be the source of elements contaminating internal compartments of the vehicle. To assure the cleanliness of the living space inside the compartments, П40463 Изм. Лист № докум. Подп. Дата Лист 154 liquid, loose and paste-like substances shall be contained within a reliable sealed package. The SE structure shall guarantee that the amount of outgassing will not exceed maximum allowable concentrations, that is, the gas composition will not be disturbed. SE shall not be a source of strong smell. The acceptable noise level during SE operation shall not exceed 65 dBA at the distance of 1 m. 6.3.2.6 Non-ionizing radiation The use of SE containing sources of laser radiation, as well as containing permanent magnets, shall be agreed with RSC Energia. 6.3.2.7 In-flight handling safety 6.3.2.7.1 SE shall have interlocks to prevent inadvertent operation or a change in configuration caused by crew actions during handling. For example, locking of Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата switches can be achieved by means of protective covers. If need be, onboard documentation (instructions) for the crew shall be prepared. 6.3.2.7.2 SE external structure and packaging shall have no sharp or protruding elements. 6.3.2.7.3 Touch temperature Surfaces having temperature of 40 to 45оC, with which the crew may come into an inadvertent contact, shall have appropriate caution plates. Surfaces with temperatures above 45оC shall have protective devices or insulation to prevent crew contact. Surfaces with temperatures below 5оC, with which the crew may come into contact shall have protective devices or insulation to prevent such contact, as well as caution plates. П40463 Изм. Лист № докум. Подп. Дата Лист 155 6.3.2.7.4 Spherical radii of outer corners and edges The SE hardware shall have rounded corners and edges, or means of protecting the corners in accordance with Table 6.3.2.7.4 Table 6.3.2.7.4 Spherical radii of outer corners, planes and edges Structural Radius, mm elements/fragments Outer Inner Holes, panels, covers 6,4 3,0 Preferable (corner radii in the panel 3,0 1,5 Minimal Note plane) Open corners 13,0 Minimal Open edges: (1) thickness of 2.0 ≥1,0 (2) (3) and more full radius; thickness of Smoothed 0.5 to 2.0 mm out or thickness of less rounded off Minimal Small pieces of hardware 1,0 Note: Instead of a spherical radius, a chamfer 450 by 1.5 mm (minimum) with Инв.№ подл. Подпись и дата Инв. № дубл. than 0.5 mm Взам. инв. № Подпись и дата mm Minimal manipulated by hand wearing a spacesuit glove smoothly beveled edges. The chamfer width shall be selected in accordance with approximate values for spherical radii described above. 6.3.2.7.5 Screws and bolts Bolts and screws with threaded parts may protrude by 2-3 mm but by no more than 1 turn of the thread, and have means of protection, which do not interfere with installation or removal of the bolt or the screw. Fasteners shall be captive. П40463 Изм. Лист № докум. Подп. Дата Лист 156 6.3.2.7.6 Moving parts Moving parts (fans, belt-drives, turbine wheels, etc.), which may cause crew injury or damage to SE through inadvertent contact or capture, shall have guard rails or other protective devices. 6.3.2.7.7 Pitch or capture points Controls, locks and other similar devices shall be designed and positioned in such a manner as to prevent them from pinching parts of the crew spacesuit. If need be, protective covers or enclosures shall be used. SE hardware located outside habitable compartments, which during its operation may produce a gap of less than 3.5 mm between the hardware and adjacent structures shall be designed in such a manner as to prevent pinching or capture of parts of spacesuit of a crew member performing an EVA. 6.3.2.7.8 SE installation Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Internal and external SE located along the crew translation paths and installed in the working areas shall be able to withstand loads caused by crew activities, including EVA. 6.3.2.8 Chemical power sources (batteries and storage batteries, electrochemical cells) The structure, materials and electrolytes used in the chemical power sources shall meet requirements of paragraphs 6.3.1 and 6.3.2.1 of these requirements. Chemical power sources and/or devices, which use them, shall have protection against charging/discharging overcurrents, excessive temperature and devices preventing discharges of electrolyte into the atmosphere of the vehicle. The use of chemical power sources with more than 120 watt-hour capacity or having especially toxic electrolytes (such as theonylchloride lithium) is only allowed upon agreement with RSC Energia П40463 Изм. Лист № докум. Подп. Дата Лист 157 Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Fig. 6.4 – A typical ISS RS crew day plan 6.4 A typical crew day plan during implementation of the standard mode П40463 Изм. Лист № докум. Подп. Дата Лист 158 6.5 Acoustic environment in the ISS RS modules ISS modules are filled with noisy equipment, which operates continuously or for long periods of time throughout the day and constitutes the backbone of the life support systems. Such systems include: ventilation system, air conditioning system, system for filtering harmful contaminants from the air, thermal control system. Immediate sources of continuous noise are such elements of these systems as fans, pumps, compressors, electrical drives for various purposes, mechanically operated controllers, etc. There are no international standards for noise levels inside habitable compartments of spacecraft. In Russia there is a currently operating standard GOST R 50804-95 Crew Habitable Environment in a Manned Spacecraft. General Medical and Technical Requirements recommendations of which, as applicable to the International Space Station became a constituent part of Russian-US standard Joint NASA/RSA Document On Specifications And Standards For The ISS Russian Segment (SSP 50094) which was put in force in 1996. Взам. инв. № Инв. № дубл. Подпись и дата Used as the unit for evaluating human exposure to noise usually is the level LA measured in decibels with scale A correction (dBA) which corrects for nonuniformity in an average human’s hearing acuity for sounds with the same level at different frequencies within the audible range. It should be noted that the noise level LA does not always give a precise characterization of the noise perception and only serves as its approximate criterion. For missions lasting more than 30 days, SSP 50094 establishes maximum allowable acoustical levels in habitable compartments of the spacecraft and methods of their measurement. According to SSP 50094, noise from continuously operating sources is restricted to the limiting acoustic pressure spectrum (in dB) in Инв.№ подл. Подпись и дата octave frequency bands with their geometric average values ranging from 31.5 to 8000 Hz, as well as to integral sound levels (LA ) and equivalent sound levels (LA,equ.), measured on the A scale in dBA. By equivalent noise level (LA,equ.) is meant a value that is equal to the constant noise level (LA), which has the same energy. With continuously operating noise sources, the acceptable noise pressure П40463 Изм. Лист № докум. Подп. Дата Лист 159 levels in octave frequency bands, acoustic levels and equivalent acoustic levels in habitable compartments of the Russian Segment of the International Space Station established separately for the crew working and sleeping modes are listed in Table 6.5.1. With the joint operation of the primary (continuous) and additional (intermittent) noise sources, the aim is to make sure that the equivalent noise level for the period of active crew operations (16 hours) does not exceed 60 dBA. And in all the cases where the equivalent sound level exceeds 60 dBA taking into account additional intermittent noise sources, the noise from all these sources shall be limited by operating time parameters of the additional equipment per Table 6.5.2. Table 6.5.1 Acceptable sound pressure levels in octave frequency bands and equivalent Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата scale-A corrected sound levels for continuous noise in the habitable compartments of manned spacecraft Mission duration of Sound pressure levels (dB) in octave Equivalent more than 30 days frequency bands noise levels and sound levels expressed in dBA Center frequencies 63 (Hz) 12 25 50 5 0 0 1k 2k 4k 8k Work (16 hours) 79 70 63 58 55 52 50 49 60* Sleep (8 hours) 71 61 54 49 45 42 40 38 50* *) These noise levels are given as rounded values, calculated for octave frequency bands. П40463 Изм. Лист № докум. Подп. Дата Лист 160 Taking into account additional intermittent noise sources, the total level of sound per day measured in dBA, and duration of exposure to it per day shall not exceed acceptable levels given in Table 2, with the equivalent level for the crew active Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата period not exceeding 60 dBA. П40463 Изм. Лист № докум. Подп. Дата Лист 161 Table 6.5.2 Maximum acceptable sound levels over a 16-hour working period in habitable compartments and in locations where the crew stays for short periods of time during operation of additional noise sources, depending on the time of exposure to them, Maximum exposure time (hours) Total acoustic pressure level (dBA) Подпись и дата over a 16-hour working period 4 63 2 66 1 69 0.5 72 Acoustic pressure levels in octave frequency bands from additional noisy equipment delivered onboard the manned spacecraft (not covered by requirements of Tables 1 and 2, but included in the payloads/scientific duration of their activation. In order to evaluate the effect of the additional equipment, in each specific case an acoustic analysis is conducted of the of noise. levels allowable per sanitary and hygienic standards during crew active duty and Инв.№ подл. Взам. инв. № mission phase, which includes this source and all the other significant sources Подпись и дата Инв. № дубл. equipment) shall be blow those given in Tables 1 and 2 depending on the The noise exposure through an entire multi-day mission, which exceeds the even during sleep, along with other adverse spaceflight factors results in higher crew fatigue and loss of hearing acuity. This circumstance, and increasingly П40463 Изм. Лист № докум. Подп. Дата Лист 162 difficult recognition of voice commands and audio warning signals against the noise background also affect flight safety. 6.5.1 Acoustic environment in the SM SM is designed in such a way as to allow the crew to continuously reside in it, and, in particular, this module has crew quarters (cabins) where crew members can sleep. After a number of measures have been implemented to reduce levels of noise from these noise sources, which included installing various devices (noise suppressors, vibration insulators, sound absorbent mats, vibration damping coatings), at present noise levels in the SM working compartment generated by the continuously operating onboard equipment, according to in-flight acoustic measurement results, are: - in the central station area ― 65 … 67 dBA; - in the wider part of the working compartment ― 64 … 65 dBA; - in crew cabins (with fully closed doors) ― 52 … 55 dBA. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата It should be kept in mind that the controlled noise levels shall correspond to a mode where only continuously operating onboard equipment is working in normal operational mode in the absence of noises from intermittent sources and in the absence of any noise generated by crew members. (It should be noted that the noise generated by crew activities is not controlled in any way at all.) 6.5.2 Acoustic environment in DC1 DC1 design allows the crew to stay in it for short periods of time. Based on the results of ground pre-flight acoustic tests, the noise level in the central part of DC1 was ~70 dBA. There were no plans to implement measures to reduce levels inside DC1. In-flight acoustic measurements produced lower values: П40463 Изм. Лист № докум. Подп. Дата Лист 163 66 … 68 dBA, which may be due to a change in acoustic properties of the internal volume of the module resulting from the fact that it is partially cluttered up with various objects (especially, soft objects). During ground tests the module was empty. 6.5.3 Acoustic environment in MRM2 MRM2 design allows the crew to stay in it for short periods of time. MRM2 geometry and configuration of its continuously operating onboard equipment are similar to DC1. Based on the results of ground pre-flight acoustic tests, the noise level in the central part of MRM2 was ~70 dBA. 6.5.2 Acoustic environment in MRM1 MRM1 design allows the crew to stay in it for short periods of time. central part of MRM1 was, when averaged along the length of the working compartment, ~72 dBA. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Based on the results of ground pre-flight acoustic tests, the noise level in the П40463 Изм. Лист № докум. Подп. Дата Лист 164 6.6 Cargo integration 6.6.1 General Progress and Soyuz spacecraft deliver to the space station “dry” cargoes in pressurized compartments. In addition to this, Progress can deliver to the station liquids and gases. If need be, cargoes can be placed outside the pressurized compartment. Cargoes transported by the vehicles shall meet requirements set fourth in this document. Documentation shall be drawn up for all the cargoes (including the packing used in flight) to state that the cargoes are allowed to be stored and operated onboard the International Space Station and transported onboard the spacecraft, as well as to certify the flight safety of the cargo. The cargo accompanying documentation and technical manuals must be approved by RSC Energia. In order for RSC Energia to perform work on integration of the cargo and to study the feasibility of its accommodation onboard the spacecraft, a documentation 6.6.1.1 For all cargoes: - envelope and installation drawing; - transportation safety data package; - accompanying documentation. 6.6.1.2 For active cargoes, additional documentation is provided in accordance with agreements between RSC Energia and the cargo owner on its integration and delivery, including: - electrical interface, including electrical consumption; Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата package is to be submitted, which contains: - heat release - cargo operations timeline; - special requirements (activation, telemetry, etc.) Requirements for envelope and installation drawing are given in paragraph 6.7.1. П40463 Изм. Лист № докум. Подп. Дата Лист 165 Requirements for transportation safety data package are given in paragraph 6.7.2. Requirements for accompanying documentation are given in paragraph 6.7.3. The cargo owner is responsible for validity of provided data and for cargo compliance with the specified requirements. Cargo delivery, removal and return are only performed in case of positive results of RSC Energia’s studies of cargo compliance with the requirements and feasibility of their accommodation and fastening. The studies are conducted on the basis of the documentation provided by the cargo owner/curator. 6.6.2 Project Management Cargo integration project management consists of the following steps: 1) reviewing and approving the documentation package on the cargoes manifested for delivery on a specific spacecraft; active cargoes require matching the interfaces; 2) engineering analysis − development of the configuration for cargo Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата accommodation in the compartment meeting the requirements for mass, centering and inertial properties of the spacecraft and conditions for cargo delivery (fastening, in-flight attitude, etc.), and the conditions stipulating that the equipment in the compartments shall not interfere with the crew operating controls and using life support equipment; 3) physical integration – building up kits, accommodating and securing cargoes in the spacecraft compartment. 6.6.3 Cargo accomodation 6.6.3.1 General The cargos are arranged within the compartments in such a way as to meet the requirements and constraints of the vehicle and of the cargoes themselves, and this arrangement is covered in the vehicle design documentation. Cargoes are installed onboard the spacecraft using RSC Energia drawings and design and operational documentation contingent upon availability of certificates П40463 Изм. Лист № докум. Подп. Дата Лист 166 for transportation and operation, and the installation is covered in the onboard documentation for the vehicle. All the operations to service and process the deliverable cargoes at the processing facility are only conducted subject to availability of proper instructions agreed with RSC Energia and under the supervision of its responsible representatives. 6.6.3.2 Conditions for placing cargoes onboard Progress spacecraft The owner/curator of the cargo shall keep in mind that after the cargo is stowed in the vehicle and until it is unstowed onboard the station, there will be no access to it. The duration of the above period depends on the conditions for stowing and installing cargoes onboard the vehicle. Deliverable cargoes are stowed in containers designed for them and in free areas within the cargo compartment. As a rule, cargoes with a mass of 8÷10 kg are stowed in the spacecraft containers (if there are no special transportation requirements), and cargoes with a higher Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата mass are installed in special transportation racks, for which purpose the deliverable unit shall have mounting fixtures. The need to develop special mounting fixtures and packaging (adapter racks, shock absorbers, thermal insulation, moisture-proofing, etc.) is stipulated when the contract is concluded. 6.6.3.3 Cargo accommodation onboard Soyuz spacecraft Deliverable cargoes are stowed in the areas within the cargo compartment that are set aside for them. As a rule, cargoes with a mass of up to 5 kg are stowed in the spacecraft containers (if there are no special transportation requirements), and cargoes with a higher mass are installed in special transportation racks, for which purpose the deliverable unit shall have mounting fixtures. П40463 Изм. Лист № докум. Подп. Дата Лист 167 The need to develop special mounting fixtures and packaging (adapter racks, shock absorbers, thermal insulation, moisture-proofing, etc.) is stipulated when the contract is concluded. The main place for accommodating payloads returning to Earth is the container under the middle seat. In the two-seater version of the spacecraft, returning payloads are also stowed in a special container installed into the right-hand seat. Returning payloads shall be capable of being loaded through the payload container cover (dimensions 170x470 mm). The decision on the feasibility of returning a cargo to Earth is made based on the results of RSC Energia study. 6.6.4 Deliverable cargo integration timeline 6.6.4.1 Deliverable cargo integration into Progress spacecraft The work to integrate cargoes into Progress spacecraft starts 6 months before the scheduled launch of the spacecraft and is based on the cargo delivery Manifest. 6 to 4 months before the spacecraft is launched, cargo outline and installation Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата drawings are submitted to RSC Energia for approval. Based on the results of the approval process for the cargo outline drawings, the feasibility of delivering cargo onboard the spacecraft is determined, and cargo delivery Manifest is updated (if necessary). 4 months before the spacecraft is launched, final outline and installation drawings of the deliverable cargos are to be submitted to the RSC Energia specialists on the spacecraft. 3 months before the launch, the specialists on the vehicle publish layout drawings for cargo accommodation inside the cargo compartment of the spacecraft, and perform a preliminary engineering analysis of mass, center of gravity, and inertial characteristics of the spacecraft. Published 1.5 months before the launch of the spacecraft are engineering drawings and documentation on cargo installation, and the results of the analysis of cargo mass, inertial, and center of gravity properties of the spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 168 No later than 1 month before the launch, the cargo is to be delivered to the processing facility, where it will then be physically integrated into the vehicle. Fig. 6.6.1 shows the process of deliverable cargo integration into Progress spacecraft. L-4 L-6 L-3 L-1.5 L-1 L Months Cargo data are submitted and approved Layout drawing is developed for cargo accommodation in the spacecraft Engineering documentation and drawings are developed Cargo delivery to the engineering À Physical integration of the cargo À Spacecraft launch Fig. 6.6.1 The process of deliverable cargo integration into Progress spacecraft. Physical integration of deliverable cargos. The process of physical integration of cargoes is determined by the technical plan of spacecraft processing at the processing facility and the launch pad. Fig. 6.5.2 shows the process of physical integration of cargos into Progress spacecraft. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата facility П40463 Изм. Лист № докум. Подп. Дата Лист 169 L-25 L-12 L-8 L-5 L-2 L-1 L Days Loading the main load of deliverable cargoes Loading additional deliverable cargos Loading additional cargo at the launch pad À The spacecraft launch Fig. 6.6.2 The process of physical integration of cargo into Progress spacecraft. The major portion of physical integration of deliverable cargo into the cargo compartment of the spacecraft is performed 25÷12 days before the launch of the spacecraft. Specific schedules for loading cargo within the specified interval of time and the number of days allocated for physical integration is determined by the Подпись и дата technical plan for specific spacecraft processing. Within the time period of 8÷5 days before the launch of the spacecraft, during final operations after the spacecraft has gone through the filling station and payload unit assembly, it is possible, by the decision of the technical management, Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. to perform additional physical integration (additional loading) of deliverable cargoes of a limited mass and volume. 2÷1 days before the spacecraft launch, it is possible, by the decision of the RSC Energia General Designer, to load additional kits of a limited size through the side loading hatch on the spacecraft. The need to integrate cargo during that time period shall be stated when the cargo delivery request is submitted for inclusion in the Manifest. 6.6.4.2 Deliverable cargo integration into Soyuz spacecraft The work to integrate cargoes into Soyuz spacecraft starts 4 months before the scheduled launch of the spacecraft and is based on the cargo delivery Manifest. П40463 Изм. Лист № докум. Подп. Дата Лист 170 4 to 3.5 months before the spacecraft is launched, cargo outline and installation drawings are submitted to RSC Energia for approval. Based on the results of the approval process for the cargo outline drawings, the feasibility of delivering cargo onboard the spacecraft is determined, and cargo delivery Manifest is updated (if necessary). 3 month before the spacecraft is launched, final outline and installation drawings of the deliverable cargos are to be submitted to the RSC Energia specialists on the spacecraft. 2.5 to 2 months before the launch, the specialists on the spacecraft publish layout drawings for cargo accommodation inside the cargo compartment of the spacecraft, and perform a preliminary engineering analysis of mass, center of gravity, and inertial characteristics of the spacecraft. Published 1.5 months before the launch of the spacecraft by specialists on the spacecraft are engineering drawings and documentation on cargo installation, and the results of the analysis of cargo mass, inertial, and center of gravity properties of No later than 1 month before the launch, the cargo is to be delivered to the processing facility, where it will then be physically integrated into the vehicle. Fig. 6.5.3 shows the process of deliverable cargo integration into Soyuz spacecraft. Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата the spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 171 L-4 L-3 L-2 L-1.5 L-1 L Months Cargo data are submitted and approved Layout drawing is developed for cargo accommodation in the spacecraft Drawings and technical Documentation is developed À Cargo delivery to the processing facility Physical integration of the cargo À Spacecraft launch Physical integration of cargoes into Soyuz spacecraft Fig. 6.5.4 shows the process of physical cargo integration into Soyuz spacecraft. L-12 L-30 L-5 L-2 L-1 L Days Loading additional deliverable cargos Loading additional cargo at the launch pad Взам. инв. № Подпись и дата L-8 Loading the main load of deliverable cargoes Инв. № дубл. Подпись и дата Fig. 6.6.3 The process of deliverable cargo integration into Soyuz spacecraft. À The spacecraft launch Fig. 6.6.4 The process of cargo integration into Soyuz spacecraft The major portion of physical integration of deliverable cargo into the orbital module and the descent vehicle of the spacecraft is performed 30÷12 days before Инв.№ подл. the launch of the spacecraft. Specific schedules for loading cargo within the П40463 Изм. Лист № докум. Подп. Дата Лист 172 specified interval of time and the number of days allocated for physical integration is determined by the technical plan for specific spacecraft processing. Within the time period of 8÷5 days before the launch of the spacecraft, during final operations after the spacecraft has gone through the filling station and payload unit assembly, it is possible, by the decision of the technical management, to perform additional physical integration (additional loading) of deliverable cargoes of a limited mass and volume. 2÷1 days before the spacecraft launch, it is possible, by the decision of the RSC Energia General Designer, to load additional kits of a limited size through the side loading hatch on the spacecraft. The need to integrate cargo during that time period shall be stated when the cargo delivery request is submitted for inclusion in the Manifest. 6.6.4.3 Safety documentation submittal deadlines Deadlines for submitting transportation safety data packages for review are: Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата −3 months before launch – for the first category cargoes (non-hazardous cargoes) and second category cargoes (the cargoes that are hazardous, but prevention measures are obvious); −4 months before the launch – for the first and second category cargoes, which require developing special fixtures for securing them onboard the spacecraft. - 6 months before the launch – for the cargoes of the third category (highly technical cargoes posing a great hazard during delivery, installation and operation), a transportation safety data package containing all the currently available information on potential hazards of the cargo must be submitted. The final complete transportation safety data package shall be submitted within the timeframe established for the first and second category cargoes. Note: Deadlines for submitting transportation safety data package for review are different from deadlines for submitting inputs for assessments and analyses. П40463 Изм. Лист № докум. Подп. Дата Лист 173 6.6.5 Integration timeline for cargoes to be disposed of Considering the need to analyze and approve documentation packages for cargoes delivered to ISS onboard the transportation vehicles of the Partners, cargo documentation packages shall be submitted to RSC Energia from the cargo owners (curators): − for approval – 1 month before spacecraft undocking from the space station; − approved – 15 days before the undocking. No documentation packages need to be submitted for the cargoes that were delivered to ISS onboard Russian vehicles. 6.6.6 Integration timeline for cargoes to be returned to Earth Defined at 3 months before spacecraft undocks from the space station is: which cargoes to be returned to Earth are to be integrated into the descent vehicle of the spacecraft in orbit. Взам. инв. № Инв. № дубл. Подпись и дата Defined at 2.5 to 2 months before spacecraft undocks from the space station is the configuration of the hardware to be returned in the order of priority. Submitted to RSC Energia shall be final documentation packages only for those cargoes, which were delivered to ISS onboard the transportation vehicles of the Partners. 1.5 to 1 month before the spacecraft undocking, RSC Energia specialists on the vehicle define the layout for cargoes to be returned to Earth. These materials are the basis for updating onboard documentation. The configuration and accommodation of the equipment to be returned can be updated using a radiogram from MCC after the Soyuz spacecraft has docked with the space station, but no later than 5 days before the scheduled landing of the descent vehicle (provided the Инв.№ подл. Подпись и дата cargo safety package is available) in consultation with RSC Energia. Fig. 6.6.5 shows the process of integrating cargoes to be returned to Earth into Soyuz spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 174 T- T- T- T- T- 75 60 45 30 21 T-7 T Days Submission of the manifest and the cargo data package Preliminary design update (layout configuration) Updating onboard documentation Uplinking a preliminary radiogram from MCC preparing cargoes for return Physical integration of the cargo to be returned into Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата the descent vehicle Docking of the next spacecraft À À Descent vehicle landing Fig. 6.5.5 The process of integration of cargo to be returned to Earth into Soyuz spacecraft 6.6.7 Documentation requirements 6.6.7.1 Requirements for the outline and installation drawing The outline and installation drawing is a drawing of a cargo (a kit, a cable) in transportation position. The outline and installation drawing shall cover the following data: 1) name; 2) drawing number; 3) mass; 4) coordinates of the center of mass (with tolerances); П40463 Изм. Лист № докум. Подп. Дата Лист 175 5) moments of inertia (with tolerances); 6) unit drawing/configuration; 7) outline dimensions (with tolerances) of the cargo, specifying dimensions of all protruding elements; 8) locations of connectors, monitoring or control panels, toggle switches; 9) coordinates of the unit attachment points and dimensions of fastener holes (for cargoes with a mass of more than 8÷10 kg.); 10) instructions for the unit orientation during transportation onboard spacecraft with respect to the flight/g-load direction, if there is such a constraint (subsection 0); 0H 11) instructions concerning the feasibility of the unit delivery inside a spacecraft container or on-the-spot accommodation; 12) special requirements for transportation conditions onboard the Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата spacecraft (if need be); 13) lifting points (for cargoes with a mass above 20 kg). 14) bar-code location If, during transportation onboard the spacecraft, the cargo is staying inside its packaging or it has temporary protective elements (covers), the outline and installation drawing shall reflect the cargo in packaging and with its protective covers. Outline and installation drawings of the cargoes shall be approved by specialists on the spacecraft (RSC Energia). In case of repeated/multiple deliveries of a cargo that has already been delivered on the same type of spacecraft in the past, no additional approval of the outline and installation drawing is required. П40463 Изм. Лист № докум. Подп. Дата Лист 176 6.6.7.2 Requirements for the safety data package In accordance with SSP 50146, cargo safety information shall be presented in the form of a safety data package. General requirements for the safety data package contents and format, as well as cargo classification by category are defined in SSP 50146, Attachment D. In order to certify cargoes for compliance with the transportation environments and transportation safety requirements, the owners of these cargoes need to prepare a transportation safety data package to reflect compliance with requirements of Section 2.5. Information about cargo hazards is considered complete, if each hazard in the transportation safety data package has: - hazard description; - measures to prevent the hazard; - methods of safety verification and documentation with verification results. Cargo ground processing safety is reviewed separately from transportation Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата safety, therefore it shall not be covered in the transportation safety data package. 6.6.7.3 Requirements for accompanying documentation Accompanying documentation is submitted to RSC Energia in Russian and in English. Accompanying documentation contains: - technical data sheet; - cargo processing instructions (if need be); - instructions for the crew (if need be). The list of accompanying documentation for an active cargo is TBD (in consultation between RSC Energia and the country supplying the cargo). The technical data sheet contains the name, the drawing number, the serial number, the useful life, as well as confirms that cargo has been fully processed and is operational (verification report), complies with specifications and is ready for flight operation within the ISS. The technical data sheet is published for each item П40463 Изм. Лист № докум. Подп. Дата Лист 177 on the deliverable cargo list, if several identical cargoes are delivered, one technical data sheet specifying their quantity is published. Fig. 6.6.6 shows the reference coordinate system of the spacecraft. Fig. 6.6.7 shows the cargo compartment of the Progress spacecraft. Fig. 6.6.8 shows the arrangement of containers in the cargo compartment of the Progress spacecraft. Fig. 6.6.9 shows dimensions of cargo containers on the Progress spacecraft. Fig. 6.6.10 shows the container and locations for accommodating additional cargo inside the orbital module of Soyuz-TMA spacecraft. Fig. 6.6.11 shows cargo container in the descent vehicle of the Soyuz-TMA Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 178 Fig. 6.6.6 Reference coordinate system of the spacecraft Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Center of mass П40463 Изм. Лист № докум. Подп. Дата Лист 179 Docking unit Access hatch Docking unit cover envelope Access hatch Подпись и дата Loading hatch Payload containers Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Payload containers Fig. 6.6.7 Cargo compartment of the Progress spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 180 Tier Tier Tier Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Container numbering scheme Fig. 6.6.8 The arrangement of containers in the cargo compartment of the Progress Инв.№ подл. spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 181 Tier III containers (No. III-1, III-2, III-3, III-4) Tier II containers (No. II-1, II-2, II-3) Подпись и дата Tier I containers Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Spacecraft assembly installation envelope Spacecraft assembly installation envelope Fig. 6.6.9 Dimensions of cargo containers of the Progress spacecraft П40463 Изм. Лист № докум. Подп. Дата Лист 182 Payload accommodation area a closet a closet Payload rack a couch Подпись и дата payload accommodation area a couch Подпись и дата Взам. инв. № Инв. № дубл. Additional cargo rack Note: 1. In containers No. 1,5,7,9 the cargo to be delivered is placed in addition to the standard equipment. 2. The payload is only placed in container No.6, when a two-seater version of the of the spacecraft is used. Fig. 6.6.10 The container and locations for accommodating additional cargo inside Инв.№ подл. the orbital module of the Soyuz-TMA spacecraft П40463 Изм. Лист № докум. Подп. Дата Лист 183 Инв. № дубл. Подпись и дата Container cover (in open position) Инв.№ подл. Подпись и дата Взам. инв. № Container cover (in open position) Fig. 6.6.11 Cargo container in the descent vehicle of the Soyuz-TMA spacecraft. П40463 Изм. Лист № докум. Подп. Дата Лист 184 Attachment A (obligatory) List of Acronyms АФУ БИЛ БИТС БКС Бортовая кабельная сеть БНО Баллистико-навигационное обеспечение БО Бытовой отсек БСР Блок сопряжения Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата БСР-ТМ Инв.№ подл. Антенно-фидерное устройство Бортовые информационные листки Бортовая информационнотелеметрическая система Блок сопряжения телеметрических массивов БТА Базовая точка активная БТП Базовая точка пассивная БТС ВЗП-У ВнеКД Базовая точка для полезной нагрузки Платформа виброзащитная универсальная Внекорабельная деятельность AFD Antenna and Feeder Device Onboard information sheets OI TS Onboard information and telemetry system Onboard cabling system OM Trajectory and navigation support Orbital Module IU Interface Unit TM IU Telemetry array interface unit Active Basepoint Passive Basepoint Payload Basepoint EVA Multipurpose vibration isolation platform Extravehiclular Activity ВЧ Высокая частота High frequency ГА Гермоадаптер Pressurized adapter Галактические космические лучи Galactic cosmic rays ГО Головной обтекатель Payload fairing ГрО Грузовой отсек Cargo compartment ИС Информационная система Information system КЭ Космические эксперименты Space experiments КЦН Комплекс целевых нагрузок ГКЛ ЛИ Летные испытания MPF Mission Payload Facility Flight tests П40463 Изм. Лист № докум. Подп. Дата Лист 185 ЛПЭ МИМ2 МИМ1 МЛМ Подпись и дата Инв. № дубл. Взам. инв. № Малый исследовательский модуль 2 Малый исследовательский модуль 1 Многофункциональный лабораторный модуль MRM2 Mini Research Module 2 Микро метеоритная защита МСС Модуль сбора сообщений Научная аппаратура Linear energy transfer MRM1 Mini Research Module 1 MLM Multi-purpose Laboratory Module Micro-meteorid shield Message collecting module SE Scientific Equipment НИП Наземный измерительный пункт Ground tracking station НШС Нештатная ситуация Off-nominal situation ОСК Орбитальная система координат ПГО Приборно грузовой отсек OCS ПН Пакет данных по безопасности Программно-математическое SW обеспечение PL Полезная нагрузка ПО Программное обеспечение ПДБ Подпись и дата LET ММЗ НА ПМО Orbital Coordinate System Instrumentation Cargo Compartment Safety data package Software Payload Software Test program ПЭИ Программа экспериментальных испытаний РО1 Рабочий отсек Working compartment Протоны радиационных поясов Земли Российской сегмент ISS RS РС МКС международной космической станции Радиотехническая система РСУС управления и связи Радиоэлектронная РЭА аппаратура РПЗ СА Инв.№ подл. Линейная передача энергии Спускаемый аппарат Earth radiation belt protons International Space Station Russian Segment RF command and communications system RF equipment Descent vehicle П40463 Изм. Лист № докум. Подп. Дата Лист 186 СБИ Система бортовых измерений СМ Служебный модуль SM Onboard measurement system Service Module СО1 Стыковочный отсек DC1 Docking Compartment СОТР СТТС СЭП ТБУ-В ТБУ-Н ТВС ТГК Инв.№ подл. Термостат биотехнологический универсальный высокотемпературный Термостат биотехнологический универсальный низкотемпературный УФП ФГБ ЦА ЦИ ЦУП-М MBLT T Multipurpose Biotechnological LowTemperature Thermostat Тяжелые заряженные частицы Транспортный грузовой корабль Heavy charged particles Ressuply spacecraft Phone Ультракороткие волны УСТТС MBHT Multipurpose T Biotechnological HighTemperature Thermostat TV-system УКВ УРМ-Д Telephone and telegraph communications system Power supply system Телевизионная система Телефон УРМ Thermal control system Система энергопитания ТЛФ Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата ТЗЧ Система обеспечения теплового режима Система телефоннотелеграфной связи Универсальное рабочее место Универсальное рабочее место доставляемое Устройство сопряжения с системой Устройство фиксации пассивное Функциональный грузовой блок Ultra-short waves MPW Multi-Purpose Workstation MPWD Multi-Purpose Workstation Deliverable System interface device Passive restraint FGB Mission payload Целевая аппаратура Payload data Целевая информация Центр управления полетами Москвы Functional cargo module MCCM Mission Control Center – Moscow П40463 Изм. Лист № докум. Подп. Дата Лист 187 ШК Airlock Шлюзовая камера ERA European robotic arm Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Европейский манипулятор П40463 Изм. Лист № докум. Подп. Дата Лист 188 modified replaced new deleted Total number of pages in the document Document number Incoming number of accompanyin g documentati on and date Data Инв.№ подл. Подпись и дата Взам. инв. № Инв. № дубл. Подпись и дата Revision Page numbers Signature REVISION LOG П40463 Изм. Лист № докум. Подп. Дата Лист 189
